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Aerodynamics, Supersonic

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Aerodynamics of supersonic flight
High-speed aerodynamics
Supersonic aerodynamics
Supersonics
Supersonic speeds

Filed under: Aerodynamics, Supersonic

Vector Polar Method for Shock Interactions With Area Disturbances (technical note DR 4; Berkeley: University of California, 1959), by Antoni K. Oppenheim and Paul A. Urtiew (page images at HathiTrust)
Wind-Tunnel Investigation at Supersonic Speeds of a Canard-Controlled Missile with Fixed and Free-Rolling Tail Fins (NASA Technical Paper 1316; 1978), by A. B. Blair (page images at HathiTrust)
Design of a very-low-bleed Mach 2.5 mixed-compression inlet with 45 percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Joseph F. Wasserbauer, Harvey E. Neumann, Robert J. Shaw, and Lewis Research Center (page images at HathiTrust)
Experimental investigation of the partial- admission performance characteristics of a single-stage Mach 2 supersonic turbine / (Washington D.C. : National Aeronautics and Space Administration, 1959), by Thomas P. Moffitt, Frederick W. Klag, and Langley Research Center (page images at HathiTrust)
Sideslip characteristics at various angles of attack for several hypersonic missile configurations with canard controls at a mach number of 2.01 / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Gerald V. Foster and Langley Research Center (page images at HathiTrust)
Pressure data for four analytically defined arrow wings in supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by James C. Townsend, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Poppet valve control of throat stability bypass to increase stable airflow range of a Mach 2.5. inlet with 60 percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1975), by Glenn A. Mitchell, Bobby W. Sanders, and Lewis Research Center (page images at HathiTrust)
Comparative flutter calculations on low-aspect-ratio wings in incompressible and supersonic flows. ([Cambridge, Mass.] M.I.T. Department of Aeronautical Engineering, 1954), by Garabed Zartarian, Herbert M. Voss, and Pao Tan Hsu (page images at HathiTrust; US access only)
Tables of supersonic conical flow / ([Dangerfield, TX : General Dynamics Corp., Convair Division, 1960]), by Ernest Carlton Kennedy, H. C. Kerr, and General Dynamics Corporation. Convair Division (page images at HathiTrust; US access only)
The NCOREL computer program for 3D nonlinear supersonic potential flow computations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Michael J. Siclari, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center, and Grumman Aerospace Corporation (page images at HathiTrust)
Lifting surfaces in supersonic flow. (Dayton, O. : Wright-Patterson air force base, Headquaters, Air materiel command, 1949-), by Simon Ostrach and W. H. Pell (page images at HathiTrust; US access only)
On the flow of a compressible fluid by the hodograph method. (Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1944), by I. E. Garrick, Carl Kaplan, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
On the flow of a compressible fluid by the hodograph method. (Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1944), by I. E. Garrick, Carl Kaplan, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Preliminary investigation of supersonic diffusers / (Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1945), by Arthur Kantrowitz, Coleman duP. Donaldson, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Two-dimensional motion of a gas at large supersonic velocities / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by S. V. Falkovich and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
On the determination of certain basic types of supersonic flow fields / (Washington, D.C. : NACA, 1954), by Carlo Ferrari and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
A summary of information on support interference at transonic and supersonic speeds / (Washington, D.C. : NACA, 1954), by Eugene S. Love, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Some examples of the applications of the transonic and supersonic area rules to the prediction of wave drag / (Washington, D.C. : NACA, 1957), by Robert L. Nelson, Clement J. Welsh, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Aircraft configurations developing high lift-drag ratios at high supersonic speeds / (Washington, D.C. : NACA, 1956), by A. J. Eggers, Clarence A. Syvertson, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
A theoretical investigation of the drag of generalized aircraft configurations in supersonic flow / (Washington, D.C. : NACA, 1957), by E. W. Graham and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
On harmonic motion of wide delta airfoils at supersonic speeds / (Inyokern, Calif. : U.S. Naval Ordnance Test Station, Research Dept., Ballistics Division, Aerodynamics Branch, [1950]), by John Miles (page images at HathiTrust)
Calculation of two-dimensional inlet flow fields by an implicit method including viscous effects - program documentation and test case / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Service], 1981), by Sedat Biringen, Oden J. McMillan, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Velocity field of a round jet in a cross flow for various jet injection angles and velocity ratios / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : for sale by the National Technical Information Service], 1979), by Richard L. Fearn, Robert P. Weston, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Bumblebee Program - aerodynamic data / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by G. A. Barnes, L. L. Cronovich, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Control of supersonic aircraft. (Wright-Patterson Air Force Base, Ohio, 1966), by Feliko Iosifovich Sklianskii (page images at HathiTrust)
Fin loads and tip-control hinge moments on a 1/8-scale model simulating the first stage of the Scout research vehicle at a mach number of 2.01 / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Ross B. Robinson, Emma Jean Landrum, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Analysis of the dynamic response of a supersonic inlet to flow-field perturbations upstream of the normal shock / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Gary L. Cole, Ross G. Willoh, and Lewis Research Center (page images at HathiTrust)
Deployment and performance characteristics of 1.5-meter supersonic attached inflatable decelerators / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Herman L. Bohon, Robert Miserentino, James Wayne Sawyer, and Langley Research Center (page images at HathiTrust)
Experimental aerodynamic performance characteristics of a rotor entry vehicle configuration : III. Supersonic / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1971), by Ronald C. Smith, Alan D. Levin, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Nonparallel instability of supersonic and hypersonic boundary layers / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Nabil M. El-Hady, Langley Research Center, and Inc Analytical Services & Materials (page images at HathiTrust)
Experimental investigation of a Mach 5 isentropic spike inlet at and below design speed / (Washington : National Aeronautics and Space Administration, [1959]), by Leonard E. Stitt, Richard J. Flaherty, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Wind-tunnel investigation of the static stability of a 1/56-scale model of the X-1E airplane at Mach numbers of 2.37, 2.98, and 4.01 / (Washington : National Aeronautics and Space Administration, [1959]), by Fred M. Smith and United States National Aeronautics and Space Administration (page images at HathiTrust)
Transonic aerodynamic characteristics of a model of a proposed six-engine hull-type seaplane designed for supersonic flight / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Dewey E. Wornom and United States National Aeronautics and Space Administration (page images at HathiTrust)
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hull-type airplane with a variable-incidence wing / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by William W. Petynia, Roger H. Fournier, Albin O. Pearson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by David N. Bowditch, William K. Tabata, Bernhard H. Anderson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effects of spoiler-slot-deflector control on the aerodynamic characteristics at a mach number of 2.01 of a variable-wing-sweep configuration with the outer wing panels swept back 75° / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Gerald V. Foster and United States National Aeronautics and Space Administration (page images at HathiTrust)
Lift, drag, and pitching moments of an arrow wing having 80° of sweepback at mach numbers from 2.48 to 3.51 and Reynolds numbers up to 11.0 million / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by Edward J. Hopkins, Alan D. Levin, Don W. Jillie, and United States National Aeronautics and Space Administration (page images at HathiTrust)
An experimental study of the flutter of sails having a delta planform tested from a Mach number of 0.1 to a Mach number of 1.9 / (Washington [D.C.] : National Aeronautics and Space Administration, [1961]), by R. W. Hess, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A second order slender wing theory for wings with leading edge separation in supersonic flow / (Washington : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1971), by Joseph P. Nenni, Chee Tung, Langley Research Center, United States National Aeronautics and Space Administration, and Cornell Aeronautical Laboratory (page images at HathiTrust)
An experimental study of slot injection into a supersonic stream / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Michael Kenworthy, Joseph A. Schetz, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
Numerical solutions of the Navier-Stokes equations for the supersonic laminar flow over a two-dimensional compression corner / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by James E. Carter and Langley Research Center (page images at HathiTrust)
Supersonic free-flight measurements of heat transfer and transition on a 10° cone having a low temperature ratio / (Washington, [D.C.] : National Aeronautical and Space Administration, 1961), by Charles F. Merlet, Charles B. Rumsey, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Static thrust augmentation of a rocket-ejector system with a heated supersonic primary jet / (Washington, [D.C.] : National Aeronautics and Space Administration, 1962), by Albert J. Simonson, James W. Schmeer, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Effects of Mach number on pitot-probe displacment in a turbulent boundary layer / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Jerry M. Allen and Langley Research Center (page images at HathiTrust)
Study of lee-side flows over conically cambered delta wings at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Richard M. Wood, Carolyn B. Watson, and Langley Research Center (page images at HathiTrust)
Effect of milling machine roughness and wing dihedral on the supersonic aerodynamic characteristics of a highly swept wing / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by Christine M. Darden and Langley Research Center (page images at HathiTrust)
NASA Aerodynamics Program : annual report 1990 / ([Washington, D.C.] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Louis J. Williams and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program (page images at HathiTrust)
Free-flight measurments [i.e. measurements] of static and dynamic stability of models of the Project Mercury re-entry capsule at Mach numbers 3 and 9.5 / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Simon C. Sommer, Dale L. Compton, Barbara J. Short, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Aerodynamic characteristics at Mach numbers from 1.6 to 2.8 of 74⁰ swept arrow wings with and without camber and twist / (Washington : National Aeronautics and Space Administration, [1959]), by Dennis F. Hasson, Norman Wong, Ann B. Fichter, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Dynamic response of a supersonic diffuser to bypass and spike oscillation / (Washington : National Aeronautics and Space Administration, [1959]), by David N. Bowditch, Fred A. Wilcox, and United States National Aeronautics and Space Administration (page images at HathiTrust)
The interaction and penetration of gaseous jets in supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1969), by R. C. Orth, F. S. Billig, J. A. Schetz, United States. Naval Ordnance Systems Command, Johns Hopkins University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Calculated effects of body shape on the bow-shock overpressures in the far field of bodies in supersonic flow / (Washington, DC : U.S. G.P.O., 1960), by Donald L. Lansing, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Effects of geometric variables on the performance of a probe for direct measurement of free-stream stagnation pressure in supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Lana M. Couch and Langley Research Center (page images at HathiTrust)
Supersonic flutter of panels loaded with inplane shear / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by James Wayne Sawyer and Langely Research Center (page images at HathiTrust)
A study of methods which predict supersonic flow fields from body geometry, distance, and Mach number / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Robert J. Mack and Langley Research Center (page images at HathiTrust)
Supersonic flutter of sandwich panels : effects of face sheet bending stiffness, rotary inertia, and orthotropic core shear stiffnesses / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Larry L. Erickson, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Lloyd S. Jernell and Langley Research Center (page images at HathiTrust)
Computer program for calculating the flow field of supersonic ejector nozzles / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Bernhard H. Anderson and Lewis Research Center (page images at HathiTrust)
Assessment of an analytical procedure for predicting supersonic ejector nozzle performance / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Bernhard H. Anderson and Lewis Research Center (page images at HathiTrust)
Exploratory investigation at mach number of 2.01 of the longitudinal stability and control characteristics of a winged reentry configuration / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by Gerald V. Foster and United States National Aeronautics and Space Administration (page images at HathiTrust)
Some effects of variations in density and aerodynamic parameters on the calculated flutter characteristics of finite-span swept and unswept wings at subsonic and supersonic speeds / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by E. Carson Yates and United States National Aeronautics and Space Administration (page images at HathiTrust)
Analysis of an emergency deceleration and descent of the XB-70-1 airplane due to engine damage resulting from structural failure / (Washington, D.C. : National Aeronautics and Space Administration, [1966]), by Chester H. Wolowicz and United States National Aeronautics and Space Administration (page images at HathiTrust)
Transonic aerodynamic damping and oscillatory stability in yaw and pitch for a model of a variable-sweep supersonic transport airplane / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1966]), by Bruce R. Wright, Benjamin T. Averett, and United States National Aeronautics and Space Administration (page images at HathiTrust)
The aerodynamic characteristics of a body in the flow field near the tip of a circular-arc wing of rectangular plan form at a mach number of 2.01 / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by John P. Gapcynski and United States National Aeronautics and Space Administration (page images at HathiTrust)
Navier-Stokes and Euler solutions for lee-side flows over supersonic delta wings : a correlation with experiment / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by S. Naomi McMillin, Earll M. Murman, James L. Thomas, and Langley Research Center (page images at HathiTrust)
The uniform-stress spinning filamentary disk / ([Washington] : National Aeronautics and Space Administration, [1964]), by A. C. Kyser, Astro Research Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Decay of strong plane shocks in an ideal gas / ([Washington] : National Aeronautics and Space Administration, [1964]), by Pei Chi Chou, Lawrence J. Zajac, Robert R. Karpp, Drexel Institute of Technology, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Condensing pressure drop by improved Lockhart-Martinelli method / ([Washington] : National Aeronautics and Space Administration, [1964]), by Fred L. Robson, Winthrop E. Hilding, University of Connecticut, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Compressibility effects on fluid entrainment by turbulent mixing layers / ([Washington] : National Aeronautics and Space Administration, [1964]), by Jacques A. F. Hill, James E. Nicholson, Inc Mithras, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Wake analysis for supersonic decelerator applications / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by Richard A. Lau, Langley Research Center, and Goodyear Aerospace Corporation (page images at HathiTrust)
Performance of an isolated two-dimensional variable-geometry wedge nozzle with translating shroud and collapsing wedge at speeds up to Mach 2.01 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Donald L. Maiden and Langley Research Center (page images at HathiTrust)
Comparisons of theoretical and experimental pressure distributions over a wing-body model at high supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1971), by Lloyd S. Jernell, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Mixing of hydrogen injected from multiple injectors normal to a supersonic airstream / (Washington : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1971), by R. Clayton Rogers, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Aerodynamics of a model of the HL-10 flight-test vehicle at Mach 0.35 to 1.80 / (Washington, D.C. : National Aeronautics and Space Administration, [1971]), by Charles L. Ladson, Acquilla S. Hill, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Coupled supersonic inlet-engine control using overboard bypass doors and engine speed to control normal shock position / (Washington : National Aeronautics and Space Administration, 1970), by Gary L. Cole, George H. Neiner, Robert E. Wallhagen, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Influence of airfoil geometry on delta wing leading-edge vortices and vortex-induced aerodynamics at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Richard M. Wood, Gary F. Wesselmann, James E. Byrd, and Langley Research Center (page images at HathiTrust)
Throat stability-bypass systems to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Glenn A. Mitchell, Robert J. Shaw, Bobby W. Sanders, and Lewis Research Center (page images at HathiTrust)
Analytical properties of noise generating mechanisms in a supersonic jet exhaust flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : Available from the National Technical Information Service, 1971), by S. Paul Pao, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Development and applications of supersonic unsteady consistent aerodynamics for interfering parallel wings / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Kari Appa, G. C. C. Smith, Langley Research Center, and Bell Aerospace Company (page images at HathiTrust)
Design of a bleed system for a Mach 3.5 inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by J. Syberg, T. E. Hickcox, Ames Research Center, and Boeing Company (page images at HathiTrust)
Unsteady aerodynamic forces on a slender body of revolution in supersonic flow / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Reuben Bond, Barbara B. Packard, and Ames Research Center (page images at HathiTrust)
Effect of speed brakes on the supersonic aerodynamic characteristics of a variable-sweep tactical fighter model at Mach numbers from 1.60 to 2.50 / (Washington, D.C. : National Aeronautics and Space Administration, 1968), by Celia S. Richardson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effect of diffusers, shrouds, and mass injection on the starting and operating characteristics of a Mach 5 free jet tunnel / (Washington : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1971), by John K. Molloy, J. Wayne Keyes, Ernest A. Mackley, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Aerodynamic characteristics of a swept-wing cruise missile at Mach numbers from 0.50 to 2.86 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by M. Leroy Spearman, Ida K. Collins, and Langley Research Center (page images at HathiTrust)
A numerical method for evaluation and utilization of supersonic nacelle-wing interference / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., 1969), by Robert J. Mack, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
On the use of magnetohydrodynamics during high speed re-entry / ([Washington, D.C.] : National Aeronautics and Space Administration, [1965]), by P. O. Jarvinen, Avco-Everett Research Laboratory, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Drag and stability characteristics of a variety of reefed and unreefed parachute configurations at Mach 1.80 with an empirical correlation for supersonic Mach numbers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Lana M. Couch and Langley Research Center (page images at HathiTrust)
Investigation of sonic boom generated by thin, nonlifting, rectangular wings / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Sanford S. Davis, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Pitot-probe displacement in a supersonic turbulent boundary layer (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1972), by Jerry M. Allen, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Evaluation of compressible-flow Preston tube calibrations / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Jerry M. Allen and Langley Research Center (page images at HathiTrust)
Analytical and experimental performance of optimal controller designs for a supersonic inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by John R. Zeller and Lewis Research Center (page images at HathiTrust)
Calculation of supersonic stream parameters of a real gas from measurable quantities using FORTRAN IV routines / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Robert C. Johnson and Lewis Research Center (page images at HathiTrust)
Performance of a Mach Number 3.0 design axisymmetric double-cone external-compression inlet in the mach number range 1.97 to 0.79 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Owen H. Davis, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
Aerodynamic characteristics at mach numbers of 1.41 and 2.01 of a series of cranked wings ranging in aspect ratio from 4.00 to 1.74 in combination with a body / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by John R. Sevier and United States National Aeronautics and Space Administration (page images at HathiTrust)
Supersonic flow past a family of blunt axisymmetric bodies / (Washington, DC : U.S. G.P.O., 1959), by Milton Van Dyke, Helen D. Gordon, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Effects of leading-edge sweep angle and design lift coefficient on performance of a modified arrow wing at a design Mach number of 2.6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Robert J. Mack and Langley Research Center (page images at HathiTrust)
Numerical methods for the design and analysis of wings at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Harry W. Carlson, David S. Miller, and Langley Research Center (page images at HathiTrust)
Investigation of net-thrust and base-pressure characteristics of cylindrical afterbodies with clustered supersonic nozzles at transonic Mach numbers / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Earl H. Andrews, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Sweep effect on the drag of rows of perpendicular circular cylinders in a laminar boundary layer at supersonic free-stream velocities / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Milton Lamb, Robert L. Stallings, and Langley Research Center (page images at HathiTrust)
Wind-tunnel investigation of paraglider models at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Robert T. Taylor and United States National Aeronautics and Space Administration (page images at HathiTrust)
Comparison of experimental and theoretical static aeroelastic loads and deflections of a thin 45° wing in supersonic flow / (Washington, [D.C.] : National Aeronautical and Space Administration, 1961), by Floyd V. Bennett, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Influence of particle drag coefficient on particle motion in high-speed flow with typical laser velocimeter applications / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1976), by Michael J. Walsh and Langley Research Center (page images at HathiTrust)
Theoretical face pressure and drag characteristics of forward-facing steps in supersonic turbulent boundary layers / (Washington : National Aeronautics and Space Administration, 1975), by D. K. Patel and K. R. Czarnecki (page images at HathiTrust)
Experimental and numerical investigation of boundary-layer development and transition on the walls of a Mach 5 nozzle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by William D. Harvey, Julius E. Harris, Aubrey M. Cary, and Langley Research Center (page images at HathiTrust)
A short static-pressure probe design for supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by S. Z. Pinckney and Langley Research Center (page images at HathiTrust)
The effects of winglets on low aspect ratio wings at supersonic Mach numbers / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by James A. Keenan, John Kuhlman, Langley Research Center, and West Virginia University. Dept. of Mechanical and Aerospace Engineering (page images at HathiTrust)
Calculation of three-dimensional, inviscid supersonic, steady flows / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by Gino Moretti, Langley Research Center, Polytechnic Institute of New York, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Some effects of mach number and geometry on sonic boom / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1967), by R. M. Hicks, Lynn W. Hunton, Joel P. Mendoza, and Ames Research Center (page images at HathiTrust)
The drag of a delta wing in supersonic flow / (Dayton, Ohio : Headquarters, Air Matériel Command, Wright-Patterson Air Force Base, 1949), by Eugene A. Carpovich, F. I. Frankl, and Brown University. Graduate Division of Applied Mathematics (page images at HathiTrust)
Pressure measurements of the leading edge of a swept wing at Mach 2.2 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Russell B. Sorrells and Langley Research Center (page images at HathiTrust)
Supersonic dynamic stability characteristics of a space shuttle orbiter / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1976), by Delma C. Freeman, Edwin E. Davenport, Richmond P. Boyden, and Langley Research Center (page images at HathiTrust)
Unsteady supersonic flow / (Baltimore, Md. : Headquarters, Air Research and Development Command, [1955]), by John W. Miles and United States. Air Force. Air Research and Development Command (page images at HathiTrust; US access only)
Proceedings of the SCAR Conference, held at Langley Research Center, Hampton, Virginia, November, 9-12, 1976. ([Washington] : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the National Technical Information Service, [1976?]), by Scar Conference (1976 : Langley Research Center) (page images at HathiTrust)
Aerodynamics of supersonic flight; an introduction. (New York, Pitman Pub. Corp., [1950]), by Alan Pope (page images at HathiTrust)
The stabilizing effectiveness of conical flares on bodies with conical noses / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by Donn B. Kirk, Gary T. Chapman, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Bibliography of Supersonic Cruise Research (SCR) Program from 1980 to 1983 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by Sherwood Hoffman and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Bibliography of Supersonic Cruise Research (SCR) Program from 1977 to mid-1980 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Sherwood Hoffman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Bibliography of supersonic cruise aircraft research (SCAR) program from 1972 to mid-1977 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the National Technical Information Service, 1977), by Sherwood Hoffman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Aerodynamic characteristics of a fixed arrow-wing supersonic cruise aircraft at Mach numbers of 2.30, 2.70, and 2.95 / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Odell A. Morris, Crolyn B. Watson, Dennis E. Fuller, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Terminal-shock and restart control of a Mach 2.5, axisymmetric, mixed compression inlet with 40 percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Robert J. Baumbick, Robert C. Seidel, Robert E. Wallhagen, and Lewis Research Center (page images at HathiTrust)
Study of supersonic wings employing the attainable leading-edge thrust concept / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by W. D. Middleton, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Boeing Commercial Airplane Company, and Langley Research Center (page images at HathiTrust)
A study of finite-difference methods as applied to hypersonic viscous shock-layer equations (Buffalo, Cornell Aeronautical Laboratory, Inc., 1963), by Angela L. Chang and Hsien Kei Cheng (page images at HathiTrust)
The calculation of three-dimensional supersonic flows around spherically-capped smooth bodies and wings ([Dayton, Ohio] Air Force Flight Dynamics Laboratory, Air Force Systems Command, Wright-Patterson Air Force Base, 1972), by Chong-Wei Chu, Sidney A. Powers, Wright-Patterson Air Force Base United States. Air Force Flight Dynamics Laboratory, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Proceedings of the SCAR Conference, held at Langley Research Center, Hampton, Virginia, November, 9-12, 1976. -- ([Washington] : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the National Technical Information Service, [1977]), by Scar Conference (1976 : Langley Research Center) (page images at HathiTrust)
Drag due to lift of a not-so-slender configuration; application of theory. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1958), by Robert J. Vidal (page images at HathiTrust)
Reduction of drag due to lift at supersonic speeds (Wright-Patterson Air Force Base, Ohio, Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1954 [i. e. 1955]), by Douglas Aircraft Company and E. W. Graham (page images at HathiTrust)
Inviscid radiating shock layers about spheres traveling at hyperbolic speeds in air / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1969), by Richard W. Barnwell, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
Base pressure coefficients obtained from the X-15 airplane for Mach numbers up to 6 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia], 1964), by Edwin J. Saltzman, United States National Aeronautics and Space Administration, and Flight Research Center (U.S.) (page images at HathiTrust; US access only)
Analysis of the linearized supersonic flow about pointed bodies of revolution by the method of characteristics / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1966), by Alan D. Sherer and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds, (Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by William A. Cassels and James F. Campbell (page images at HathiTrust; US access only)
Investigation of a mixed-compression axisymmetric inlet system at Mach numbers 0.6 to 3.5, (Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by Donald B. Smeltzer and Norman E. Sorensen (page images at HathiTrust; US access only)
Analysis of supersonic conical flows / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1970), by C. W. Chiang, Richard D. Wagner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
An inverse-method solution for radiating, nonadiabatic, equilibrium inviscid flow over a blunt body / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1970), by Ralph A. Falanga, Edward M. Sullivan, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Splitting supersonic nozzle flow into separate jets by overexpansion into a multilobed divergent nozzle / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by Ronald G. Huff, Donald E. Groesbeck, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Blunt body solutions for spheres and ellipsoids in equilibrium gas mixtures / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1965), by Mamoru Inouye, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Measurements of the Mach number and pressure on the afterbody of a blunt-nosed model in free flight at Mach numbers from 6.5 to 14 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Simon C. Sommer and Ames Research Center (page images at HathiTrust)
Tables of supersonic flow around cones of large yaw, (Cambridge, 1949), by Massachusetts Institute of Technology. Dept. of Electrical Engineering. Center of Analysis and Zdeněk Kopal (page images at HathiTrust; US access only)
On the similar solutions of strong blast-waves and their application to steady hypersonic flow. ([Ithaca, N.Y.], 1961), by Eric François Brocher (page images at HathiTrust; US access only)
Aerodynamic tip theory of a supersonic propeller. ([Ithaca, N.Y.], 1958), by Richard W. 1933- Hale (page images at HathiTrust; US access only)
Critical regimes of supersonic jet aircraft; stall and spin, ([Washington] National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., [1969]), by Mikhail Grigorʹevich Kotik (page images at HathiTrust; US access only)
Numerical solution of the equations for compressible laminar, transitional, and turbulent boundary layers and comparisons with experimental data / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1971), by Julius E. Harris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Calculation of nonlinear conical flows by the method of lines / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1971), by E. B. Klunker, Ruby M. Davis, Jerry C. South, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Power- and cross-spectra and space-time correlations of surface fluctuating pressures at Mach numbers between 1.6 and 2.5 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va. 22151], 1969), by Wei J. Chyu, Richard D. Hanly, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
A method for predicting pressures on elliptic cones at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by George E. Kaattari, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
A semiempirical fracture analysis for small surface cracks / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Thomas W. Orange, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Flight measurements of canard loads, canard buffeting, and elevon and wing-tip hinge moments on the XB-70 aircraft including comparisons with predictions / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Jerald M. Jenkins, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Optical study of sonic and supersonic jet penetration from a flat plate into a Mach 2 airstream / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Martin Hersch, Frederick P. Povinelli, Louis A. Povinelli, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Real-air data-reduction procedures based on flow parameters measured in the test section of supersonic and hypersonic facilities / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by Charles G. Miller, Sue E. Wilder, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
The problem of roughness drag at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 2215], 1966), by K. R. Czarnecki, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Experimental panel flutter results for some flat and curved titanium skin panels at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1963), by John G. Presnell, R. L. McKinney, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Airborne simulation for the SST. ([Buffalo?, 1963]), by W. O. Breuhaus (page images at HathiTrust)
On the use of impact theory for slender configurations exhibiting flow separation / (Palo Alto, Calif. : Vidya, a division of Itek Corp., 1963), by Alvin Howard Sacks and Jack A Burnell (page images at HathiTrust)
Quasi-three-dimensional supersonic viscid/inviscid interactions including separation effects : final report for period, 1 October 1972- 30 September 1975 / (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1975), by Veer N Vetsa, Michael Joseph Werle, and University of Cincinnati. Aerospace Engineering Dept (page images at HathiTrust)
Nonsteady discharge of subcritical flow / (Princeton, N.J. : Project Squid Headquarters, James Forrestal Research Center, Princeton University, 1960), by George Rudinger and Project Squid (page images at HathiTrust)
Investigation of small surface protuberances upstream of turbulent boundary layer separation produced by a skewed shock wave at Mach 3 / (Wright-Patterson Air Force Base, Ohio : Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Syspems Command, 1976), by Robert H Korkegi and Air Force Aero Propulsion Laboratory (U.S.) Ramjet Technology Branch (page images at HathiTrust)
Pressure distribution on a body a revolution in supersonic flight, by Robert R. Reynolds. ([Washington, U. S. Dept. of Commerce, National Bureau of Standards], 1952), by Robert Ramon Reynolds (page images at HathiTrust)
Reverse flow and supersonic interference. ([Providence, Division of Engineering, Brown University], 1958), by Joseph H. Clarke (page images at HathiTrust)
RAXJET : a computer program for predicting transonic, axisymmetric flow over nozzle afterbodies with supersonic jet exhausts / (Washington, D.C. : U.S. National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by Richard G. Wilmoth and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
A theory for base pressures in transonic and supersonic flow / (Urbana, Ill. : Mechanical Engineering Dept., Univ. of Illinois, 1955), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust; US access only)
Truncated cone in supersonic flight at zero angle of attack : surface pressure coefficients, drag coefficients, and shock front configurations / (Urbana, Ill. : Mechanical Engineering Dept., Engineering Experiment Station, University of Illinois, Jan. 1960), by W. L. Chow, C.C. Tsung, Helmut Hans Korst, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust; US access only)
A theory for base pressures in transonic and supersonic flow / (Urbana, Ill. : Mechanical Engineering Dept., Univ. of Illinois, May 1962), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust; US access only)
Compressible two-dimensional jet mixing at constant pressure : tables of auxiliary functions for fully developed mixing profiles / (Urbana, Ill. : Mechanical Engineering Dept., University of Illinois, April 1955), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust; US access only)
Fluctuating loads measured on an over-the-wing supersonic jet model / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Conrad M. Willis, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Langley Research Center (page images at HathiTrust)
Longitudinal aerodynamic characteristics of an elliptical body with a horizontal tail at mach numbers 2.3 to 4.63 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by Barrett L. Shrout, A. Warner Robins, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
The wedge hot-film anemometer in supersonic flow / (Washington, D.C. National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by John M. Seiner, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Control of shock wave - boundary layer interactions by bleed in supersonic mixed compression inlets / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Michael K. Fukuda, Eli Reshotko, Warren R. Hingst, Lewis Research Center, and Case Western Reserve University (page images at HathiTrust)
Static stability and control characteristics of two large-dihedral right triangular pyramid lifting reentry configurations at a mach number of 3.05 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Charles F. Whitcomb, Willard E. Foss, and Langley Research Center (page images at HathiTrust)
Stability and control characteristics at a mach number of 1.89 of a lightweight glider reentry configuration / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Ross B. Robinson, M. Leroy Spearman, and Langley Research Center (page images at HathiTrust)
Experimental cavity pressure distributions at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Robert L. Stallings, Floyd J. Wilcox, and Langley Research Center (page images at HathiTrust)
Multiscale turbulence effects in supersonic jets exhausting into still air / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Khaled S. Abdol-Hamid, Richard G. Wilmoth, and Langley Research Center (page images at HathiTrust)
Planform effects on the supersonic aerodynamics of multibody configurations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by S. Naomi McMillin, Richard M. Wood, and Langley Research Center (page images at HathiTrust)
A performance index approach to aerodynamic design with the use of analysis codes only / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1988), by Raymond L. Barger, Anutosh Moitra, and Langley Research Center (page images at HathiTrust)
Supersonic aerodynamics of delta wings / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1988), by Richard M. Wood and Langley Research Center (page images at HathiTrust)
A method for computing supersonic flow around blunt bodies, accompanied by a detached shock wave / (Washington, D.C. : National Aeronautics and Space Administration, [1965]), by S. M. Gilinskiĭ, G. P. Tini︠a︡kov, and G. F. Telenin (page images at HathiTrust)
Three dimensional flow around blunt bodies by a supersonic stream of perfect gas / (Washington, D.C. : National Aeronautics and Space Administration, [1965]), by I︠U︡. N. Dʹi︠a︡konov (page images at HathiTrust)
Fuselage design for a specified Mach-sliced area distribution / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Raymond L. Barger, Mary S. Adams, and Langley Research Center (page images at HathiTrust)
Longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Laurence D. Leavitt, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Investigation of flow characteristics over missle bodies at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Raymond L. Barger, Wallace C. Sawyer, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Supersonic wings with significant leading-edge thrust at cruise / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by A. Warner Robins, Robert J. Mack, Harry W. Carlson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Supersonic stability and control characteristics of a cruciform missile model with delta wings and aft tail fin controls / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : for sale by the National Technical Information Service], 1979), by William A. Corlett, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Surface pressure data on a series of conical forebodies at mach numbers from 1.70 to 4.50 and combined angles of attack and sideslip / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by James C. Townsend and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Effect of ratio of wall boundary-layer thickness to jet diameter on mixing of a normal hydrogen jet in a supersonic stream / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Charles R. McClinton and Langley Research Center (page images at HathiTrust)
Investigation of leading-edge flap performance on delta and double-delta wings at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Peter F. Covell, David S. Miller, Richard M. Wood, and Langley Research Center (page images at HathiTrust)
Progress in supersonic cruise aircraft technology / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Office, 1978), by Cornelius Driver and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Supersonic longitudinal aerodynamic characteristics of two space shuttle orbiter configurations / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by James C. Ellison and United States National Aeronautics and Space Administration (page images at HathiTrust)
Efficient solutions to the Euler equations for supersonic flow with embedded subsonic regions / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Robert W. Walters, Douglas L. Dwoyer, and Langley Research Center (page images at HathiTrust)
Performance and surge limits of a TF30-P-3 turbofan engine/axisymmetric mixed-compression inlet propulsion system at Mach 2.5 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Joseph F. Wasserbauer, Robert J. Shaw, Harvey E. Neumann, and Lewis Research Center (page images at HathiTrust)
Evaluation of some control-volume techniques for analysis of shock-boundary-layer interactions in supersonic inlets / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Warren R. Hingst and Lewis Research Center (page images at HathiTrust)
Instantaneous distortion in a Mach 2.5, 40-percent-internal-contraction inlet and its effect on turbojet stall margin / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Paul L. Burstadt, James E. Calogeras, and Lewis Research Center (page images at HathiTrust)
Optical measurement of static temperature and hydroxyl radical profiles in a hydrogen-fueled supersonic combustor / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Raymond E. Gaugler and Lewis Research Center (page images at HathiTrust)
An experimental investigation of nacelle-pylon installation on an unswept wing at subsonic and transonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by John R. Carlson, William B. Compton, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Body and canard effects on an attached-flow maneuver wing at Mach 1.62 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by Jimmy L. Pittman, William H. Mason, David S. Miller, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Surface pressure data for a supersonic-cruise airplane configuration at mach numbers of 2.30, 2.96, and 3.30 / (Greenbelt, Md. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va : For sale by the National Technical Information Service], 1979), by Barrett L. Shrout, Ida K. Collins, William A. Corlett, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Correlations of supersonic boundary-layer transition on cones including effects of large axial variations in wind-tunnel noise / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by Fang-Jenq Chen, Theodore R. Creel, Ivan E. Beckwith, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Experimental investigation of leading-edge thrust at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Richard M. Wood, D. S. Miller, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Terminal-shock and restart control of a Mach 2.5, mixed-compression inlet coupled to a turbofan engine / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Robert J. Baumbick, Carl J. Daniele, Peter G. Batterton, and Lewis Research Center (page images at HathiTrust)
Control system design using frequency domain models and parameter optimization, with application to supersonic inlet controls / (Washington, D.C., National Aeronautics and Space Administration, 1974), by Robert C. Seidel, Bruce Lehtinen, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
Effect of leading-edge load constraints on the design and performance of supersonic wings / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Christine M. Darden and Langley Research Center (page images at HathiTrust)
The natural flow wing-design concept / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Richard M. Wood, Steven X. S. Bauer, and Langley Research Center (page images at HathiTrust)
Measurements of sonic booms generated by an airplane flying at Mach 3.5 and 4.8 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Karen S. Green, Terrill W. Putnam, and Flight Research Center (U.S.) (page images at HathiTrust)
Continuous-output terminal-shock-position sensor for mixed-compression inlets evaluated in wind-tunnel tests of YF-12 aircraft inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Miles O. Dustin, George H. Neiner, Gary L. Cole, and Lewis Research Center (page images at HathiTrust)
Experimental investigation of a simple distortion index utilizing steady-state and dynamic distortions in a Mach 2.5 mixed-compression inlet and turbofan engine / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by William G. Costakis and Lewis Research Center (page images at HathiTrust)
Longitudinal and lateral-directional aerodynamic characteristics of a wing-cone configuration at Mach numbers from 2.5 to 4.5 / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Peter F. Covell, Dorothy T. Howell, Ira J. Walker, and Langley Research Center (page images at HathiTrust)
Reevaluation of compressible-flow Preston tube calibrations / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Jerry M. Allen and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effect of Reynolds number on the aerodynamic stability and control characteristics of a 55 ̊clipped-delta-wing orbiter configuration at supersonic mach numbers / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by A. B. Blair, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Computer program for supersonic kernel-function flutter analysis of thin lifting surfaces / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Herbert J. Cunningham and Langley Research Center (page images at HathiTrust)
User's guide for a computer program for calculating the zero-lift wave drag of complex aircraft configurations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Charlotte B. Craidon and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Supersonic aerodynamic characteristics of a series of wrap-around-fin missile configurations / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Roger H. Fournier and United States National Aeronautics and Space Administration (page images at HathiTrust)
Theoretical evaluation of high-speed aerodynamics for arrow-wing configurations / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Samuel M. Dollyhigh, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Aerodynamic characteristics at Mach numbers from 0.6 to 2.16 of supersonic cruise fighter configuration with a design Mach mumber of 1.8 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Barrett L. Shrout and United States National Aeronautics and Space Administration (page images at HathiTrust)
Comparison of two computer programs by predicting turbulent mixing of helium in a ducted supersonic airstream / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Y. S. Pan, Charles R. McClinton, John Philip Drummond, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Forebody and afterbody solutions of the Navier-Stokes equations for supersonic flow over blunt bodies in a generalized orthogonal coordinate system / ([Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978), by Peter A. Gnoffo (page images at HathiTrust)
Mechanical characteristics of stability-bleed valves for a supersonic inlet / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by George H. Neiner, Gary L. Cole, Miles O. Dustin, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Application of a two-dimensional unsteady viscous analysis code to a supersonic throughflow fan stage / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by Ronald J. Steinke and Lewis Research Center (page images at HathiTrust)
Supersonic aerodynamic characteristics of a proposed assured crew return capability (ACRC) lifting-body configuration / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by George M. Ware and Langley Research Center (page images at HathiTrust)
Low-speed static and dynamic force tests of a generic supersonic cruise fighter configuration / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by David E. Hahne and Langley Research Center (page images at HathiTrust)
Cold-flow acoustic evaluation of a small-scale, divergent, lobed nozzle for supersonic jet noise suppression / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Ronald G. Huff, Donald E. Groesbeck, and Lewis Research Center (page images at HathiTrust)
Performance of vortex generators in a Mach 2.5 low-bleed full-scale 45-percent-internal-contraction axisymmetric inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Harvey E. Neumann, Robert J. Shaw, Joseph F. Wasserbauer, and Lewis Research Center (page images at HathiTrust)
A study of the sonic-boom characteristics of a blunt body at a Mach number of 4.14 / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield Va. : For sale by the National Technical Information Service, 1977), by Harry W. Carlson, Robert J. Mack, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Effects of roughness size on the position of boundary-layer transition and on the aerodynamics characteristics of a 55 ̊swept delta wing at supersonic speeds / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Robert L. Stallings, Milton Lamb, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
A method for calculating a real-gas two-dimensional nozzle contour including the effects of gamma / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles B. Johnson, Lillian R. Boney, and Langley Research Center (page images at HathiTrust)
Theoretical and experimental flow fields for a supersonic cruise fighter forebody / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Steven F. Yaros and Langley Research Center (page images at HathiTrust)
A modificiation to linearized theory for prediction of pressure loadings on lifting surfaces at high supersonic Mach numbers and large angles of attack / (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Harry W. Carlson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Evaluation by step response tests of prototype relief valves designed for YF-12 inlet stability bleed system / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Miles O. Dustin, George H. Neiner, and Lewis Research Center (page images at HathiTrust)
Effects of spanwise nozzle geometry and location on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Laurence D. Leavitt, Long P. Yip, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Effect of afterburner lights and inlet unstarts on a mixed-compression-inlet turbofan engine operating at Mach 2.5 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Robert J. Baumbick, Carl J. Daniele, Peter G. Batterton, and Lewis Research Center (page images at HathiTrust)
Aerodynamic characteristics of a Sparrow III missile model in the flow field of a generalized parent body at Mach 2.86 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Robert L. Stallings and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
An experimental and analytical study of the aerodynamic interference effects between two Sears-Haack bodies at Mach 2.7 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Jeffrey W. Bantle and Langley Research Center (page images at HathiTrust)
Supersonic dynamic-stability derivatives of the space shuttle launch vehicle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1976), by Richmond P. Boyden, Edwin E. Davenport, Delma C. Freeman, and Langley Research Center (page images at HathiTrust)
Some observations on a new numerical method for solving the Navier-Stokes equations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Ajay Kumar, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Experimental and theoretical supersonic lateral-directional stability characteristics of a simplified wing-body configuration with a series of vertical-tail arrangements / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Milton Lamb, James L. Thomas, Wallace C. Sawyer, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Theoretical and experimental investigation of supersonic aerodynamic characteristics of a twin-fuselage concept / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Richard M. Wood, Kenneth S. Brentner, D. S. Miller, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
A study of the sonic-boom characteristics of a blunt body at a Mach number of 6 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by George C. Ashby, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Mechanical property characterization of Borsic®/aluminum laminates at room and elevated temperatures / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Robert R. McWithey, Dick M. Royster, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Bobby L. Berrier, Richard J. Re, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Experimental and theoretical aerodynamic characteristics of two hypersonic cruise aircraft concepts at Mach numbers of 2.96, 3.96, and 4.63 / ([Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Jimmy L. Pittman, Gregory D. Riebe, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Steady and nonsteady supersonic turbulent afterbody flow / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Kenneth K. Yoshikawa, Alan A. Wray, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Ames Research Center (page images at HathiTrust)
Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Robert L. Stallings, Milton Lamb, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Aerodynamic tests and analysis of a turbojet-boosted launch vehicleconcept (spacejet) over a Mach number range of 1.50 to 2.86 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Gregory D. Riebe, Odell A. Morris, William J. Small, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Experimental investigation of porous-floor effects on cavity flow fields at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Floyd J. Wilcox and Langley Research Center (page images at HathiTrust)
Effect on tail-fin span on stability and control characteristics of a canard-controlled missile at supersonic Mach numbers / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by A. B. Blair, Gloria Hernandez, Jerry M. Allen, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Low-speed aerodynamic characteristics of a highly swept, untwisted, uncambered arrow wing / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For the sale by the National Technical Information Service], 1983), by Paul L. Coe, Garl L. Gentry, Scott O. Kjelgaard, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Combustion of hydrogen-air jets in local chemical equilibrium : (a guide to the CHARNAL computer program) / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by D. B. Spalding, Langley Research Center, and Fluid Mechanics and Thermal Systems (page images at HathiTrust)
Effect of interjet spacing on mixing of multiple coaxial jets in supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by A. K. Lorber, Joseph A. Schetz, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
The development of a three-dimensional partially elliptic flow computer program for combustor research / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Y. S. Pan, Pittsburgh Energy Research Center, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Development of the triplet singularity for the analysis of wings and bodies in supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by F. A. Woodward, Inc Analytical Methods, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Viscous computations of cold air/air flow around scramjet nozzle afterbody / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Oktay Baysal, Walter C. Englelund, Old Dominion University. Dept. of Mechanical Engineering and Mechanics, and Langley Research Center (page images at HathiTrust)
Some divergence characteristics of low-aspect-ratio wings at transonic and supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Donald S. Woolston, Herbert J. Cunningham, Frederick W. Gibson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Experimental investigation of the influence of the turbulent boundary layer on the pressure distribution over a rigid two-dimensional wavy wall / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1971]), by Lado Muhlstein, Richard G. Beranek, George C. Marshall Space Flight Center, and Ames Research Center (page images at HathiTrust)
Heat-transfer measurements at a Mach number of 2 in the turbulent boundary layer on a flat plate having a stepwise temperature distribution / (Washington : National Aeronautics and Space Administration, [1959]), by Raul J. Conti and Langley Research Center (page images at HathiTrust)
Jet effects on cylindrical afterbodies housing sonic and supersonic nozzles which exhaust against a supersonic stream at angles of attack from 90 ̊to 180 ̊/ (Washington : National Aeronautics and Space Administration, [1962]), by Lovick O. Hayman, Russell W. McDearmon, and Langley Research Center (page images at HathiTrust)
Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 / (Washington : National Aeronautics and Space Administration, [1960]), by Charles B. Rumsey, Russell N. Hopko, Robert Owens Piland, and Langley Research Center (page images at HathiTrust)
Aerodynamic performance and static stability at mach number 3.3 of an aircraft configuration employing three triangular wing panels and a body equal length / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Carlton S. James and Ames Research Center (page images at HathiTrust)
Investigation of the flow over simple bodies at Mach numbers of the order of 20 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Arthur Henderson and Langley Research Center (page images at HathiTrust)
Experimental nozzle expansion and flow characteristics of potassium vapor / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1966]), by Louis J. Goldman, Stanley M. Nosek, and Lewis Research Center (page images at HathiTrust)
Measurements of flow properties in the vicinity of three wing-fuselage combinations at Mach numbers of 1.61 and 2.01 / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Harry W. Carlson and Langley Research Center (page images at HathiTrust)
The lateral and directional aerodynamic characteristics of a re-entry configuration based on a blunt 13° half cone at Mach numbers to 0.90 / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by George C. Kenyon and Ames Research Center (page images at HathiTrust)
Transonic and supersonic flutter trend investigation of a variable-sweep wing / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by John C. Stonesifer, Robert C. Goetz, and Langley Research Center (page images at HathiTrust)
Low-speed investigation of the aerodynamic characteristics of a variable-sweep supersonic transport configuration having a blended wing and body / (Washington, D.C. : National Aeronautics and Space Administration, [1961]), by William C. Sleeman, A. Warner Robins, and Langley Research Center (page images at HathiTrust)
A method for calculating the aerodynamic loading on wing-body combinations at small angles of attack in supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Charlie M. Jackson, Wallace C. Sawyer, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Thermoelastic damping and its effect on flutter of stressed panels situated in a supersonic airflow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by R. C. Shieh, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Investigation of variation in base pressure over the Reynolds number range in which wake transition occurs for two-dimensional bodies at Mach numbers from 1.95 to 2.92 / (Washington : National Aeronautics and Space Administration, [1959]), by Vernon Van Hise and Langley Research Center (page images at HathiTrust)
Spectrographic temperature measurements in a carbon-arc-powered air jet / (Washington : National Aeronautics and Space Administration, [1959]), by David H. Greenshields and Langley Research Center (page images at HathiTrust)
Aerodynamic loading characteristics of a 1/10-scale model of the three-stage Scout vehicle at Mach numbers 1.57 to 4.65 / (Washington : National Aeronautics and Space Administration, [1963]), by Lloyd S. Jernell and Langley Research Center (page images at HathiTrust)
Effects of Reynolds number and flow incidence on the force characteristics of a family of flat-front cylinders / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Vernard E. Lockwood, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Static thrust of an annular nozzle with a concave central base / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Blake W. Corson, Charles E. Mercer, and United States National Aeronautics and Space Administration (page images at HathiTrust)
An analysis of nuclear-rocket nozzle cooling / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by William H. Robbins, Arthur A. Medeiros, Daniel Bachkin, and Lewis Research Center (page images at HathiTrust)
Flutter of flat rectangular orthotropic panels with biaxial loading and arbitrary flow direction / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1963]), by Herman L. Bohon and United States National Aeronautics and Space Administration (page images at HathiTrust)
Supersonic investigation of nozzle hinge moments of a modified Saturn C-1 model with and without jet flow / (Washington, D.C. : National Aeronautics and Space Administration, [1963]), by Nickolai Charczenko, Jerry L. Lowery, and Langley Research Center (page images at HathiTrust)
Loads induced on a flat plate at a Mach number of 4.5 with a sonic or supersonic jet exhausting normal to the surface / (Washington : National Aeronautics and Space Administration, [1963]), by William Letko and Langley Research Center (page images at HathiTrust)
Static aerodynamic characteristics of three rocket-vehicle configurations at Mach numbers from 1.80 to 4.63 including some effects of fin size, fin cant, and auxiliary rocket motors / (Washington : National Aeronautics and Space Administration, [1963]), by Dennis E. Fuller, Gerald V. Foster, and Langley Research Center (page images at HathiTrust)
Application of Dorodnitsyn's integral method to nonequilibrium flows over pointed bodies / (Washington : National Aeronautics and Space Administration, [1963]), by Jerry C. South and Langley Research Center (page images at HathiTrust)
Static stability characteristics of models of the Blue Scout and the Blue Scout, Jr., research vehicles at Mach numbers from 2.29 to 3.75 / (Washington : National Aeronautics and Space Administration, [1963]), by Lloyd S. Jernell and Langley Research Center (page images at HathiTrust)
Performance of three isentropic all internal compression axisymmetric inlets designed for Mach 2.5 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Bernhard H. Anderson, David N. Bowditch, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Stability and control characteristics at mach numbers of 2.50, 3.00, and 3.71 of a variable- wing-sweep configuration with outboard wing panels swept back 75° / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Gerald V. Foster, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Experimental and calculated supersonic flutter characteristics of models of the x-15 horizontal and vertical tails / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by William T. Lauten, R. W. Hess, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Transonic and supersonic ejection release characteristics of six dynamically scaled external-store shapes from an 0.086-scale model of a current fighter airplane / (Washington D.C. : National Aeronautics and Space Administration, 1959), by William F. Hinson and Langley Research Center (page images at HathiTrust)
Stability and control characteristics at low subsonic speeds of an airplane configuration having two types of variable-sweep wings / (Washington D.C. : National Aeronautics and Space Administration, 1960), by Bernard Spencer and Langley Research Center (page images at HathiTrust)
The effects of wing-tip droop on the aerodynamic characteristics of a delta-wing aircraft at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Richard H. Peterson and Ames Research Center (page images at HathiTrust)
Investigation of the subsonic and supersonic release characteristics of an externally carried fuel tank from a 1/40-scale model of a bomber airplane / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by William F. Hinson and Langley Research Center (page images at HathiTrust)
An experimental pressure-distribution investigation of interference effects produced at a Mach number of 3.11 by wedge- shaped bodies located under a triangular wing / (Washington D.C. : National Aeronautics and Space Administration, 1959), by Lowell E. Hasel and Langley Research Center (page images at HathiTrust)
Heat-transfer measurements on a blunt spherical-segment nose to a Mach number of 15.1 and flight performance of the rocket-propelled model to a Mach number of 17.8 / (Washington D.C. : National Aeronautics and Space Administration, 1959), by Charles B. Rumsey, Dorothy B. Lee, and Langley Research Center (page images at HathiTrust)
Mixing of supersonic jets including the effects of transvere pressure gradient using difference methods / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Anatole P. Kurkov, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
Wing planform effects at supersonic speeds for an advanced fighter configuration / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by National Technical Information Service], 1984), by Richard M. Wood, D. S. Miller, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Theoretical and experimental engine-inlet flow fields for fighter forebodies / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by Steven F. Yaros and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Transonic and supersonic Euler computations of vortex-dominated flow fields about a generic fighter / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Aga M. Goodsell, John E. Melton, and Ames Research Center (page images at HathiTrust)
Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by A. Robert Porro and Lewis Research Center (page images at HathiTrust)
Measurements of forces, moments, and pressures on a generic store separating from a box cavity at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Robert L. Stallings, Dana K. Forrest, Floyd J. Wilcox, and Langley Research Center (page images at HathiTrust)
Experimental aerodynamic characteristics at Mach numbers from 0.60 to 2.70 of two supersonic cruise fighter configurations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Samuel M. Dollyhigh, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Lee-side flow over delta wings at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by David S. Miller, Richard M. Wood, and Langley Research Center (page images at HathiTrust)
Supersonic aerodynamic characteristics of canard, tailless, and aft-tail configurations for two wing planforms / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Peter F. Covell and Langley Research Center (page images at HathiTrust)
Estimation of wing nonlinear aerodynamic characteristics at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Harry W. Carlson, Robert J. Mack, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Aerodynamic characteristics of a supersonic fighter aircraft model at Mach 0.40 to 2.47 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Francis J. Capone, Dorothy Arbiter, E. Ann Bare, and Langley Research Center (page images at HathiTrust)
Concept development of a Mach 3.0 high-speed civil transport / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by A. Warner Robins and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by A. B. Blair and United States National Aeronautics and Space Administration (page images at HathiTrust)
Supersonic aerodynamic characteristics of a Sparrow III type missile model with wing controls and comparison with existing tail-control results / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by William J. Monta and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Experimental investigation to validate use of cryogenic temperatures to achieve high Reynolds numbers in boattail pressure testing / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by David E. Reubush, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Effects of Reynolds number and model support on the supersonic aerodynamic chacteristics of a 140° included-angle cone / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Charles D. Trescot, Dorothy T. Howell, Clarence A. Brown, and Langley Research Center (page images at HathiTrust)
Pressure-activated stability-bypass-control valves to increase the stable airflow range of a Mach 2.5 inlet with 40 percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Glenn A. Mitchell, Bobby W. Sanders, and Lewis Research Center (page images at HathiTrust)
Forward-slanted slot throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Robert J. Shaw, Bobby W. Sanders, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
Distributed porous throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60 percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Robert J. Shaw, Bobby W. Sanders, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
Distributed educated throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Robert J. Shaw, Bobby W. Sanders, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
Modification of a three-dimensional supersonic nozzle analysis and comparison with experimental data / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Allan R. Bishop, Bobby W. Sanders, and Lewis Research Center (page images at HathiTrust)
Comparison of theoretical and experimental boundary-layer development in a Mach 2.5 mixed-compression inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Warren R. Hingst, Charles E. Towne, and Lewis Research Center (page images at HathiTrust)
Aerodynamic characteristics of a hypersonic research airplane concept having a 70 ̊swept double-delta wing at Mach number 0.2 / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Jim A. Penland, James L. Dillon, Theodore R. Creel, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Numerical simulation of steady supersonic viscous flow / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Lewis B. Schiff, Joseph L. Steger, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Ames Research Center (page images at HathiTrust)
Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by David S. Miller, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Experimental evaluation of a Mach 3.5 axisymmetric inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1975]), by J. Syberg, J. L. Koncsek, Ames Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations : volume II - code description / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Frank Marconi, Larry Yaeger, United States National Aeronautics and Space Administration, Langley Research Center, and Grumman Aerospace Corporation (page images at HathiTrust)
A computational system for aerodynamic design and analysis of supersonic aircraft : part 3-computer program description / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by W. D. Middleton, Robert Griffin Coleman, J. L. Lundry, United States National Aeronautics and Space Administration, Boeing Company, and Langley Research Center (page images at HathiTrust)
Equilibrium chemical reaction of supersonic hydrogen-air jets : the Alma computer program / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : S. Elghobashi and D.B. Spalding.), by S. Elghobashi, D. B. Spalding, Fluid Mechanics and Thermal Systems, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A computational system for aerodynamic design and analysis of supersonic aircraft : part 1-general description and theoretical development / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by W. D. Middleton, J. L. Lundry, United States National Aeronautics and Space Administration, Boeing Company, and Langley Research Center (page images at HathiTrust)
A computational system for aerodynamic design and analysis of supersonic aircraft : part 2, user's manual / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by W. D. Middleton, Robert Griffin Coleman, J. L. Lundry, Boeing Commercial Airplane Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Combustion of hydrogen injected into a supersonic airstream (the ship computer program) / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by N. C. Markatos, D. G. Tatchell, D. B. Spalding, Fluid Mechanics and Thermal Systems, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A System for aerodynamic design and analysis of supersonic aircraft. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by R. G. Coleman, J. L. Lundry, W. D. Middleton, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
An improved supersonic, three-dimensional, external, inviscid flow field code / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Frank Marconi, Frank Koch, Grumman Aerospace Corporation, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
An improved version of NCOREL : a computer program for 3-D nonlinear supersonic potential flow computations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Michael J. Siclari and Langley Research Center (page images at HathiTrust)
Effects of mach number and wall-temperature ratio on turbulent heat transfer at mach numbers from 3 to 5, ([Washington, U.S. G.P.O.], 1959), by Thorval Tendeland (page images at HathiTrust)
Jet effects at supersonic speeds on base and afterbody pressures of a missile model having single and multiple jets / (Washington, D.C. : National Aeronautics and Space Administration, [1963]), by Nickolai Charczenko, Clyde Hayes, and Langley Research Center (page images at HathiTrust)
Flight test and analysis of the rolling motions of a 79 ̊clipped delta configuration with wing-tip fins at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1963), by James L. Raper, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Static stability and separation characteristics of a two-stage rocket configuration at Mach numbers from 1.57 to 4.50 / (Washington : National Aeronautics and Space Administration, [1960]), by Kenneth L. Turner, Laurence W. Enderson, David S. Shaw, and Langley Research Center (page images at HathiTrust)
Supersonic longitudinal stability characteristics of the two final stages of a four-stage launch vehicle / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1964]), by Royce L. McKinney and Langley Research Center (page images at HathiTrust)
An experimental investigation of the flow in an axisymmetric internal-compression inlet for M=2.75 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1961]), by Earl C. Watson, William P. Peterson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Hypersonic viscous drag on cones in rarefied flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by M. I. Kussoy, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Turbulence measurements in supersonic, shock-free jets by the optical crossed-beam method / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., 1970), by M. J. Fisher, K. D. Johnston, United States National Aeronautics and Space Administration, George C. Marshall Space Flight Center, and IIT Research Institute (page images at HathiTrust)
Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 / (Washington : National Aeronautics and Space Administration, [1961]), by Robert W. Cubbison, James J. Ward, Bernhard H. Anderson, and Lewis Research Center (page images at HathiTrust)
Supersonic aerodynamic characteristics of a low-drag aircraft configuration having an arrow wing of aspect ratio 1.86 and a body of fineness ratio 20 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Warren Gillespie Jr. and Langley Research Center (page images at HathiTrust)
Flutter of buckled, simply supported, rectangular panels at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Robert W. Fralich, John A. McElman, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Static aerodynamic characteristics, pressure distributions, and RAM-air inflation of attached inflatable decelerator models at Mach 3.0 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by William D. Deveikis, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Systematic study of error sources in supersonic skin-friction balance measurements / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Jerry M. Allen, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Effect of nonlifting empennage surfaces on single-engine afterbody/nozzle drag at Mach numbers from 0.5 to 2.2 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Bobby L. Berrier and United States National Aeronautics and Space Administration (page images at HathiTrust)
Performance of several conical convergent-divergent rocket-type exhaust nozzles / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by C. E. Campbell, J. M. Farley, and Lewis Research Center (page images at HathiTrust)
Performance of a mass-flux probe in a Mach 3 stream / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by Lloyd N. Krause, George E. Glawe, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Joseph F. Wasserbauer, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Experimental preston tube and law-of-the-wall study of turbulent skin friction on axisymmetric bodies at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Jerry M. Allen, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
An improved method for calculating supersonic pressure fields about bodies of revolution / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Robert J. Mack, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
A study of helium penetration and spreading in a Mach 2 airstream using a delta wing injector / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1969), by Louis A. Povinelli, Martin Hersch, Frederick P. Povinelli, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A study of the application of heat or force fields to the sonic-boom-minimization problem / (Washington, D.C. : National Aeronautics and Space Administration, 1969), by David S. Miller, Harry W. Carlson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A structural merit function for aerodynamic decelerators / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Melvin S. Anderson, Martin M. Mikulas, Herman L. Bohon, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
An approximate solution of additive-drag coefficient and mass-flow ratio for inlets utilizing right circular cones at zero angle of attack / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Vincent R. Mascitti, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Supersonic aerodynamics of large-angle cones / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by James F. Campbell, Dorothy T. Howell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A mathematical analysis of supersonic inlet dynamics / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1968), by Ross G. Willoh, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
Application of a one-strip integral method to the unsteady supersonic aerodynamics of an inclined flat surface / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by Robert M. Bennett, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Design and performance of a digital electronic normal shock position sensor for mixed-compression inlets / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by Gary L. Cole, Michael J. Crosby, George H. Neiner, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
Experimental heat-transfer distributions on a blunt lifting body at Mach 3.71 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1970]), by Robert L. Stallings, Ida K. Collins, Robert L. Wright, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Calculated pressure distributions and components of total-drag coefficients for 18 constant-volume slender bodies of revolution at zero incidence for Mach numbers from 2.0 to 12.0, with experimental aerodynamic characteristics for three of the bodies / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Louis S. Stiver, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Concentration measurements of an injected gas in a supersonic stream / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1967]), by Marvin G. Torrence and Langley Research Center (page images at HathiTrust)
An exploratory investigation in a ballistic range of the stability derivatives of a simple airplane configuration at low supersonic speeds / (Washington : National Aeronautics and Space Administration, [1959]), by Charles E. DeRose, Alfred G. Boissevain, and Ames Research Center (page images at HathiTrust)
Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1969), by Helmut F. Butze, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
A method for calculating aerodynamic loadings on thin wings at a Mach number of 1 / (Washington : National Aeronautics and Space Administration), by John L. Crigler and Langley Research Center (page images at HathiTrust)
Investigation of the aerodynamic characteristics of two preliminary designs of Scout research vehicle at Mach numbers from 1.77 to 4.65 / (Washington : National Aeronautics and Space Administration, [1961]), by Robert J. Keynton, Ann B. Fichter, and Langley Research Center (page images at HathiTrust)
Accuracy of pitot-pressure rakes for turbulent boundary-layer measurements in supersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1971), by Earl R. Keener, Edward J. Hopkins, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Correlation of secondary sonic and supersonic gaseous jet penetration into supersonic crossflows / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1971]), by Frederick P. Povinelli, Louis A. Povinelli, and Lewis Research Center (page images at HathiTrust)
Some fluid mechanical problems related to subsonic and supersonic aircraft; report to the NASA Subcommittee on Fluid Mechanics of the Committee on Basic Research. (Washington, Scientific and Technical Information Division, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1968), by United States. National Aeronautics and Space Administration. Ad Hoc Committee on Subsonic and Supersonic Aeronautics and John T. Howe (page images at HathiTrust; US access only)
Some effects of flight path and atmospheric variations on the boom propagated from a supersonic aircraft / (Washington, D.C. : National Aeronautics and Space Administration, 1964), by Raymond L. Barger, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
Theoretical studies of supersonic two-dimensional and axisymmetric nonequilibrium flow, including calculations of flow through a nozzle / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1963), by James J. Der, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Flow-field measurements downstream of two protuberances on a flat plate submerged in a turbulent boundary layer at Mach 2.49 and 4.44 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Lana M. Couch, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
A theoretical analysis of the flutter of orthotropic panels exposed to a high supersonic stream of arbitrary direction / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1966), by Peter A. Gaspers, Bass Redd, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
A method of characteristics for steady three-dimensional supersonic flow with application to inclined bodies of revolution / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by John V. Rakich, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
A summary of results on sonic-boom pressure-signature variations associated with atmospheric conditions / (Washington, D.C. : National Aeronautics and Space Administration, 1968), by I. E. Garrick, Domenic J. Maglieri, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Effect of face-sheet stiffness on buckling of curved plates and cylindrical shells of sandwich construction on axial compression / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1965), by Robert E. Fulton, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Some aerodynamic and control studies of lifting reentry configurations at angles of attack up to 90° at a mach number of 2.91 / (Washington [D.C.] : National Aeronautics and Space Administration, 1960), by Frank L. Clark, Joanna M. Evans, and Langley Research Center (page images at HathiTrust; US access only)
Supersonic mixing of hydrogen and air / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1967), by John H. Morgenthaler, Johns Hopkins University, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Flow and acoustic characteristics of subsonic and supersonic jets from convergent nozzle / (Washington, D.C. : National Aeronautics and Space Administration, 1970), by Henry T. Nagamatsu, M. S. Gill, R. E. Sheer, United States National Aeronautics and Space Administration, and General Electric Company. Research and Development Center (page images at HathiTrust; US access only)
A supersonic/hypersonic aerodynamic investigation of the Saturn IB/Apollo upper stage / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by David R. Carlson and William P. Walters (page images at HathiTrust; US access only)
A direct method for calculation of the flow about an axisymmetric blunt body at angle of attack / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by Ihor O. Bohachevsky and Robert E. Mates (page images at HathiTrust; US access only)
An analytical study of the measured wall pressure field under supersonic turbulent boundary layers / (Washington, D.C. : National Aeronautics and Space Administration, 1968), by Thomas J. Black (page images at HathiTrust; US access only)
The method of characteristics for three-dimensional real-gas flows, including the digital computer program details and operating procedures for frozen flows ([Wright-Patterson Air Force Base, Ohio, Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1967]), by Charles R. Strom (page images at HathiTrust; US access only)
Effect of shape changes on the aerodynamic characteristics of a twisted and cambered arrow wing at Mach number 2.03 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by Emma Jean Landrum, Barrett L. Shrout, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Exploratory investigation of flow field resulting from forward-facing nozzles exhausting near a large cylindrical body at free-stream Mach numbers of 3.0 and 6.0 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1969), by Robert J. McGhee, James A. Martin, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Linearized theory of conical supersonic flow with application to triangular wings / ([Los Angeles?] : North American Aviation, Engineering Dept., 1946, revisions 1947), by North American Aviation and Wallace D. Hayes (page images at HathiTrust)
Some considerations of sonic boom. ([Washington, 1961]), by United States. Federal Aviation Agency. Office of Plans (page images at HathiTrust)
Studies on the validity of the hydraulic analogy to supersonic flow (Wright-Patterson Air Force Base, Dayton, Ohio, U. S. Air Force, Air Material Command, 1950-52 [pt. 1, rev. 1951]), by Massachusetts Institute of Technology. Department of Civil Engineering and Donald R. F. Harleman (page images at HathiTrust)
The shock tube as an instrument for the investigation of transonic and supersonic flow patterns : a report on work done under Office of Naval Research contract N6-ONR-232 between April, 1947 and June, 1949 / (Washington, [1949]), by Frederick William Geiger, Charles William Mautz, and University of Michigan. Office of Research Administration (page images at HathiTrust)
Material presented at the NACA Conference on Supersonic Aerodynamics at Ames Aeronautical Laboratory on June 4, 1946, National Advisory Committee for Aeronautics. ([Washington?, 1946?]), by United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Supersonic aerodynamics and rocket propulsion, (Los Angeles, c1963]), by Robert F. Lee (page images at HathiTrust)
An investigation of the exact solutions of the linearized equations for the flow past conical bodies, ([Ypsilanti, Michigan] University lithoprinters, 1948), by Otto Laporte, Robert Christian Frank Bartels, and University of Michigan. Office of Research Administration (page images at HathiTrust)
Elements of aerodynamics of supersonic flows. (New York : Macmillan Co., 1949), by Antonio Ferri (page images at HathiTrust)
Handbook of supersonic aerodynamics. (Washington, Bureau of Ordnance, 1950-), by Silver Spring Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust)
NACA Conference on High-Speed Aerodynamics; a compilation of the papers presented, Amers Aeronautical Laboratory, Moffett Field, Calif., March 18, 19, and 20, 1958. ([Washington?, 1958?]), by United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Supersonic aeroelastic effects on static stability and control. Flight Control Laboratory. Contract nos. AF33 (616)-3577 and AF33(616)-6067. ARDC Project no. 8219. Task no. 82158. (Wright-Patterson Air Force Base, Ohio, Wright Air Development Division, Air Research and Development Command., U. S. Air Force, 1958-60), by Bell Aircraft Corporation and Vincent W. Donato (page images at HathiTrust)
Supersonic wind tunnel tests of ring-wing configurations /, by Leon H. Schindel, United States. Air Force. Air Research and Development Command. sponsor, and Wright Air Development Center issuing body (page images at HathiTrust)
Supersonic flutter trends as revealed by piston theory calculations /, by Holt Ashley, Garabed Zartarian, United States. Air Force. Air Research and Development Command. sponsor, and Wright Air Development Center issuing body (page images at HathiTrust)
Survey on heat transfer at high speeds /, by E. R. G. Eckert, sponsor United States. Air Force. Air Research and Development Command, and issuing body Wright Air Development Center (page images at HathiTrust)
Effects of the upstream influence of a shock wave at supersonic speeds in the presence of a separated boundary layer /, by Lloyd E. Daniels, H. Yoshihara, sponsor United States. Air Force. Air Research and Development Command, and issuing body Wright Air Development Center (page images at HathiTrust)
Survey of boundary layer heat transfer at high velocities and high temperatures /, by E. R. G. Eckert, United States. Air Force. Air Research and Development Command. sponsor, Wright Air Development Center issuing body, University of Minnesota, and United States. Department of the Air Force. Wright Air Development Center (page images at HathiTrust)
The hypersonic facility of the Polytechnic Institute of Brooklyn and its application to problems of hypersonic flight /, by Antonio Ferri, Paul A. Libby, United States. Air Force. Air Research and Development Command. sponsor, Wright Air Development Center issuing body, and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
Supersonic mixing of jets and turbulent boundary layers /, by Harry E. Bailey, Arnold M. Kuethe, United States. Air Force. Air Research and Development Command. sponsor, and Wright Air Development Center (page images at HathiTrust)
Theoretical investigations of sonic boom phenomena /, by Raimond A. Struble, A. Ritter, E. A. Brown, C. E. Stewart, United States. Air Force. Air Research and Development Command. sponsor, Defense Documentation Center (U.S.), Wright Air Development Center, and Armour Research Foundation (U.S.). Fluid Dynamics Branch (page images at HathiTrust)
Supersonic panel flutter /, by Yudell L. Luke, Andrew St. John, United States. Air Force. Air Research and Development Command. sponsor, Midwest Research Institute, and Wright Air Development Center (page images at HathiTrust)
Solution of the potential equation for the unsteady flow about a triangular wing with subsonic leading edges in a supersonic main stream /, by Yudell L. Luke, Frank Wagner, Geraldine V. Coombs, United States. Air Force. Air Research and Development Command. sponsor, Midwest Research Institute, and Wright Air Development Center (page images at HathiTrust)
Experimental pressure distributions over wing tips at Mach number 1.9. (Washington, D.C. : National Advisory Committee for Aeronautics, [1949]), by Harold Mirels, James M. Jagger, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Line-vortex theory for calculation of supersonic downwash / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Harold Mirels, Rudolph C. Haefeli, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
High speed aerodynamics and jet propulsion. (Princeton, N.J., Princeton University Press, 195?-) (page images at HathiTrust)
Supersonic inlet diffusers and introduction to internal aerodynamics. (Minneapolis, Minneapolis-Honeywell Regulator Co., Aeronautical Division, [1956]), by Rudolf Hermann (page images at HathiTrust)
Analytical investigation of fuel temperatures and fuel-evaporation losses encountered in long-range high-altitude supersonic flight / (Washington, D.C. : National Advisory Committee for Aeronautics, [1953]), by Richard J. McCafferty, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Location of detached shock wave in front of a body moving at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1947]), by Edmund V. Laitone, Otway O'M. Pardee, and United States. National Advisory Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Combustion of aluminum borohydride in a supersonic wind tunnel / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by Edward A. Fletcher, Melvin Gerstein, Robert G. Dorsch, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Development of flow distortions in a full-scale nacelle inlet at mach numbers 0.63 and 1.6 to 2.0 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1956), by Thomas G. Piercy, Bruce G. Chiccine, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Pressure measurements on a body of revolution in the Langley 16-foot transonic tunnel and a comparison with free-fall data / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Joseph M. Hallissy, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Longitudinal aerodynamic characteristics of a model airplane configuration equipped with a scaled X-1 airplane wing / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by James H. Parks, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Mitchel H. Bertram, William D. McCauley, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation of the effects of model scale and stream Reynolds number on the aerodynamic characteristics of two rectangular wings at supersonic speeds on the Langley 9-inch supersonic tunnel / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Factors affecting the maximum lift-drag ratio at high supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1956), by Charles H. McLellan, Robert W. Dunning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Aerodynamic characteristics over a Mach number range of 1.40 to 2.78 of a rocket-propelled airplane configuration having a low 52.2©� delta wing and an unswept horizontal tail. / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Alan B. Kehlet, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Some effects of fin plan form on the static stability of fin-body combinations at Mach number 4.06 / (Washington, D.C. : National Advisory Committee for Aeronautics, XXXX), by Edward F. Ulmann, Robert W. Dunning, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
The static and dynamic longitudinal stability characteristics of some supersonic aircraft configurations / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Jesse L. Mitchell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Three-degree-of-freedom evaluation of the longitudinal transfer functions of a supersonic canard missile configuration including changes in forward speed / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Ernest C. Seaberg, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Stability of two rocket-propelled models having aspect-ratio-5 unswept tails on a long body for the Mach number range of 1.7 to 2.4 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Reginald R. Lundstrom, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Theoretical lift and damping in roll of thin sweptback wings of arbitrary taper and sweep at supersonic speeds : Subsonic leading edges and trailing edges / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Frank S. Malvestuto, H. S. Ribner, Kenneth Margolis, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Experimental investigation of temperature recovery factors on bodies of revolution at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by William R. Wimbrow and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Rolling and yawing moments for swept-back wings in sideslip at supersonic sppeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Seymour Lampert and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Supersonic lift and pitching moment of thin sweptback tapered wings produced by constant vertical acceleration. Subsonic leading edges and supersonic trailing edges / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Frank S. Malvestuto, Dorothy M. Hoover, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Axisymmetric supersonic flow in rotating impellers / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Arthur W. Goldstein and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Theoretical prediction of the side force on stores attached to configurations traveling at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1956), by Percy J. Bobbitt, Kenneth Margolis, Frank S. Malvestuto, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Final design of Sandia's supersonic parachute test vehicle / ([Albuquerque, N. M. ; Livermore, Calif. : Sandia National Laboratories ; Springfield, Va. : National Technical Information Service, 1960]), by M.T. Kane, B. L. Barth, and Sandia Corporation (page images at HathiTrust)
A Method for determining the aerodynamic characteristics of two- and three-dimensional shapes at hypersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1948), by H. Reese Ivey, Edward N. Bowen, E. Bernard Klunker, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Characteristics of a free supersonic helium jet issuing normally from a flat plate / ([Albuquerque, N.M.] : Sandia Corporation ; Washington, D.C. : Available from the Office of Technical Services, Department of Commerce, [1960]), by A. Bedford and Sandia Corporation (page images at HathiTrust)
High-speed computing machine calculation of supersonic axisymmetric flows /, by Martha W. Clark, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
Estimation of the static aerodynamic characteristics of ordnance projectiles at supersonic speeds /, by Robert L. McCoy and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
An expansion of tables II and III of N.A.C.A. TN no. 1428., by U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
Supersonic magnus measurements of the 10-Caliber Army-Navy spinner projectile with wrap-around fins /, by Frank J Regan, Virginia L. Schermerhorn, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Three-dimensional inviscid flow about supersonic blunt cones at angle of attack., by G. Moretti, U.S. Atomic Energy Commission, Nassau County General Applied Science Laboratories (Westbury, and Sandia Corporation (page images at HathiTrust)
A Program for computing steady inviscid three-dimensional supersonic flow on reentry vehicles : volume I : analysis and programming /, by J. M. Solomon, A. B Wardlaw, J. B. Bell, R. E. Ferguson, M. Ciment, and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
Sonic limit singularities:, by G. S. S Ludford, Steven H. Schot, College Park. Institute for Fluid Dynamics and Applied Mathematics University of Maryland, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Three-dimensional inviscid flow about supersonic blunt cones at angle of attack., by M. J. Abbett, R. Fort, U.S. Atomic Energy Commission, Nassau County General Applied Science Laboratories (Westbury, and Sandia Corporation (page images at HathiTrust)
Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99. (Washington, D.C. : National Advisory Committee for Aeronautics, [1951]), by L. J. Obery, G. W. Englert, United States. National Advisory Committee for Aeronautics. NACA research memorandum, United States. National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
The use of perforated inlets for efficient supersonic diffusion / (Washington : National Advisory Committee for Aeronautics, [1951]), by John C. Evvard, John W. Blakey, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Evaluation of five conical center-body supersonic diffusers at several angles of attack / (Washington, D.C. : National Advisory Committee for Aeronautics, [1952]), by Gerald W. Englert, Leonard J. Obery, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Investigation of three types of supersonic diffuser over a range of Mach numbers from 1.75 to 2.74 / (Washington, D.C. : National Advisory Committee for Aeronautics, [1951]), by L. Eugene Baughman, Larence I. Gould, United States. National Advisory Committee for Aeronautics. NACA research memorandum, United States. National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Application of oblique-shock sensing system to ram-jet-engine flight Mach number control / (Washington [D.C.] : National Aeronautics and Space Administration, [1955]), by Fred A. Wilcox, Donald P. Hearth, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Preliminary attempts at isothermal compression of a supersonic air stream / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by E. Perchonok, F. Wilcox, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation at supersonic and subsonic Mach numbers of auxiliary inlets supplying secondary air flow to ejector exhaust nozzles / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by Donald P. Hearth, Robert W. Cubbison, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Criteria for initial flow reversal in symmetrical twin-intake air-induction systems operating at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by Andrew Beke, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study. (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Harold E. Rohlik, Herbert W. Scibbe, William T. Wintucky, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation at supersonic speeds of the compressor stall and inlet buzz characteristics of a J34 - spike-inlet combination / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by J. Cary Nettles, Robert C. Campbell, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Design and experimental investigation of a single-stage turbine with a rotor entering relative Mach number of 2 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Thomas P. Moffitt, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Airplane motions and loads induced by flying through the flow field generated by an airplane at low supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Gareth H. Jordan, Stanley P. Butchart, Earl R. Keener, Flight Research Center (U.S.), United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Dynamics of a supersonic inlet with adjustable bypass in combination with a J34 turbojet engine / (Washington [D.C.] : National Advisory Committee for Aeronautics, [1956]), by Fred A. Wilcox, Paul Whalen, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Eugene S. Love, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by John D. Morrow, Ellis Katz, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and a 40©� sweepback : pressure distribution measurements of the interference effect of the wing on the fuselage at Mach numbers of 1.40 and 1.59 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by John P. Gapcynski, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and James W. Clark (page images at HathiTrust)
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch at M = 2.0 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Ross B. Robinson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Investigation of the variation with Reynolds number of the base, wave, and skin-friction drag of a parabolic body of revolution (NACA RM-10) at Mach numbers of 1.62, 1.93, and 2.41 in the Langley 9-inch supersonic tunnel / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Eugene S. Love, August F. Bromm, Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Eugene S. Love, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Investigations at supersonic speeds of the base pressure on bodies of revolution with and without sweptback stabilizing fins / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Eugene S. Love, Robert M. O'Donnell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Average skin-friction coefficients from boundary-layer measurements on an ogive-cylinder body in flight at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by J. Dan Loposer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Investigation of the drag of blunt-nosed bodies of revolution in free flight at Mach numbers from 0.6 to 2.3 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Harvey A. Wallskog, Roger G. Hart, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
A combined aerodynamic and guidance approach for a simple homing system / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Robert A. Gardiner, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Factors affecting transition at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by K. R. Czarnecki, Archibald R. Sinclair, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation at supersonic speeds of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag of seven boattail bodies of revolution designed for minimum wave drag / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by August F. Bromm, Julia M. Goodwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Some measurements at subsonic speeds of the aerodynamic forces and moments on two delta wings of aspect ratios 2 and 4 oscillating about the midchord / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Sumner A. Leadbetter, Sherman A. Clevenson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Some internal-flow characteristics at zero flight speed of an annular supersonic inlet and an open-nose inlet with sharp and rounded lips / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Joseph R. Milillo, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
A method for designing low-drag nose-inlet-body combinations for operation at moderate supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Robert R. Howell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Charles B. Rumsey, Russell N. Hopko, Robert O. Piland, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Charles B. Rumsey, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Span loadings due to wing twist at transonic and supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Frederick C. Grant, John P. Mugler, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Experimental determination of damping in pitch of swept and delta wings at supersonic Mach numbers / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by John A. Moore, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
An initial experimental study of the effect of variations in frequency and impulse on the reduction in temperature recovery factor afforded by large-scale unsteady flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Robert R. Howell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Investigation of fixed-geometry supersonic inlets with bypass ducts for matching turbojet-engine air-flow requirements over a range of transonic and supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Abraham Leiss, Walter J. Kouyoumjian, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Paul G. Fournier, Andrew L. Byrnes, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Performance of external-compression bump inlet at Mach numbers of 1.5 to 2.0 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Paul C. Simon, Ronald G. Huff, Dennis W. Brown, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Theoretical study of air forces on an oscillating or steady thin wing in a supersonic main stream / (Washington, D.C. : National Advisory Committee for Aeronautics, 1947), by I. E. Garrick, S. I. Rubinow, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Volterra's solution of the wave equation as applied to three-dimensional supersonic airfoil problems / (Washington, D.C. : National Advisory Committee for Aeronautics, 1947), by Max A. Heaslet, Arthur L. Jones, Harvard Lomax, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Use of a characteristic surfaces for unsymmetrical supersonic flow problems / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by W. E. Moeckel and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
The yawing moment, due to sideslip of triangular, trapezoidal, and related plan forms in supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Arthur L. Jones, Alberta Alksne, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
On two-dimensional supersonic flows / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1949), by Stefan Bergman and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of aspect ratio on undamped torsional oscillations of a thin rectangular wing in supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Charles E. Watkins and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Improvement of accuracy of balanced-pressure indicators and development of an indicator calibrating machine / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by James C. Livengood and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Theoretical relations between the stability derivatives of a wing in direct and in reverse supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Sidney M. Harmon and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
The reversibility theorem for thin airfoils in subsonic and supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Clinton E. Brown and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Theoretical loading at supersonic speeds of flat swept-back wings with interacting trailing and leading edges / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Doris Cohen and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Damping in roll of cruciform and some related delta wings at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by H. S. Ribner and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Turbulent boundary-layer temperature recovery factors in two-dimensional supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Maurice Tucker, Stephen H. Maslen, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Applications of Von Karman's integral method in supersonic wing theory / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Chieh-Chien Chang and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Transient aerodynamic behavior of an airfoil due to different arbitrary modes of nonstationary motions in a supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Chieh-Chien Chang and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Some theoretical characteristics of trapezoidal wings in supersonic flow and a comparison of several wing-flap combinations / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Robert O. Piland and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Dean R. Chapman, Robert H. Kester, William R. Wimbrow, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
A wind-tunnel test technique for measuring the dynamic rotary stability derivatives including the cross derivatives at high Mach numbers / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by Benjamin H. Beam and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Some effects of aircraft configuration on static longitudinal and directional stability characteristics at supersonic Mach numbers below 3 / (Washington, [D.C.] : National Advisory Committee for Aeronautics, [1959]), by M. Leroy Spearman, Arthur Henderson, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Wind-tunnel investigation of the static longitudinal and lateral stability of a 1/62-scale model of the X-1E at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by Arthur Henderson and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
A pivoting-cowl-and-spike technique for efficient angle-of-attack operation of supersonic inlets / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Nick E. Samanich, Robert W. Cubbison, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Lowell E. Hasel, Archibald R. Sinclair, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
The proper combination of lift loadings for least drag on a supersonic wing / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by Frederick C. Grant and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Coleman duP. Donaldson, Roy H. Lange, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Flow over a slender body of revolution at supersonic velocities / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1946), by Robert T. Jones, Kenneth Margolis, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
An Experimental investigation of the effect of surface heating on boundary-layer transition on a flat plate in supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Robert W. Higgins, Constantine C. Pappas, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a diamond-plan-form wing aspect ration 3.08 and a low, swept horizontal tail /, by Alan B. Kehlet, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Measurement of recovery factors and friction coefficients for supersonic flow of air in a tube. [Part] II., by Joseph Kaye, Robert Howard Shoulberg, Tau-Yi Toong, Massachusetts Institute of Technology. Division of Industrial Cooperation, and United States. Office of Naval Research (page images at HathiTrust)
Methods for conducting short-time tensile, creep, and creep-rupture tests under conditions of rapid heating /, by Donald P. Moon, Ward F. Simmons, Defense Metals Information Center (U.S.) issuing body, and United States. Office of the Director of Defense Research and Engineering (page images at HathiTrust)
On hypersonic blunt body flow fields obtained with a time-dependent technique /, by John D. Anderson, Allen E. Winkelmann, Lorenzo M. Albacete, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Slot jet interaction studies of an ogive cylinder at M[infinity] = 4 and 5 /, by R. E. Phinney, W. C. Volz, J. Knott, Michael J Werle, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
A fine-wire stagnation temperature probe /, by William Joseph Yanta and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
The use of a laser doppler velocimeter in supersonic flow /, by William Joseph Yanta, Francis W. Brown, David F. Gates, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Three-dimensional inviscid flow about supersonic blunt cones at angle of attack., by G. Moretti, G. Bleich, U.S. Atomic Energy Commission, Nassau County General Applied Science Laboratories (Westbury, and Sandia Corporation (page images at HathiTrust)
Inverse-method and method-of-characteristics flow-field programs /, by J. B. Moreno, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust)
Surface flow angles on an ogive cylinder at angle of attack in supersonic flow /, by Harold R Vaughn, Oscar L. George, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
an Investigation of the use of holography in studying supersonic flow in inlets. /, by III Spring, W. C. Ragsdale, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Sonic limit singularities:, by G. S. S Ludford, Steven H. Schot, College Park. Institute for Fluid Dynamics and Applied Mathematics University of Maryland, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
YF-12 Experiments Symposium / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : for sale by the National Technical Information Service, 1978), by YF-12 Experiments Symposium (1978 : Dryden Flight Research Center) and James and Associates (page images at HathiTrust)
Estimation of damping in roll of wings at high supersonic speeds ... ([Princeton, 1948]), by Edward Seckel (page images at HathiTrust; US access only)
On the hypersonic flow over a delta wing with very supersonic leading edges / (Los Angeles, Calif. : North American Aviation Inc., Los Angeles Division, 1965), by Norman D Malmuth and North American Aviation (page images at HathiTrust; US access only)
Subsonic and supersonic flutter analysis of a highly tapered swept-wing planform, including effects of density variation and finite wing thickness, and comparison with experiments / (Washington, D.C. : National Aeronautics and Space Administration, 1967), by E. Carson Yates, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
Pressure gradient effects on supersonic boundary layer turbulence : final report /, by A. J. Laderman, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Ford Aerospace & Communications Corporation. Fluid Mechanics Section (page images at HathiTrust)
Computer program for design and/or analysis of two-dimensional and axisymmetric inlets /, by Larry K. Ratliff and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Proceedings of Retardation and Recovery Symposium /, by Peter R. Murray, L. E. Winebrenner, and issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
Determination of the supersonic additive drag of several similar inlet configuration of the type used in the F-111 /, by Donald A. Watne and issuing body United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
Supersonic flow about general three-dimensional blunt bodies., by A. Martellucci, Paul A. Libby, Nassau County General Applied Science Laboratories (Westbury, and issuing body United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
The Mark IV Supersonic-Hypersonic Arbitrary-body Program., by Arvel E. Gentry, Wayne R. Oliver, Douglas N. Smyth, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Douglas Aircraft Company (page images at HathiTrust)
Compilation and correlation of model starting loads from several supersonic wind tunnels / ([Albuquerque, N.M. : Sandia Corporation ;, 1962]), by R. C. Maydew, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust; US access only)
Uniqueness of solution of the problem of supersonic flow past a wedge / ([Providence, R.I.] : Graduate Division of Applied Mathematics, Brown University, 1948), by F. I. Frankl (page images at HathiTrust)
Handbook of supersonic aerodynamics. (Washington, Bureau of Ordnance, 1950-), by Silver Spring Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust)
Tables for supersonic flow of helium around right circular cones at zero angle of attack, (Washington, Scientific and Technical Information Office, National Aeronautics and Space Administration; [for sale by the Supt. of Docs., U. S. Govt. Print. Off.], 1973), by Joseph L Sims and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust; US access only)
Climatology of the upper air as related to the design and operation of supersonic aircraft (Washington, U.S. Dept. of Commerce, Weather Bureau, 1963), by National Weather Records Center (U.S.) and Harold L. Crutcher (page images at HathiTrust)
Engineering supersonic aerodynamics. (New York, McGraw-Hill, 1950), by E Arthur Bonney (page images at HathiTrust)
Heat transfer to blunt nose shapes with laminar boundary layers at high supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1957]), by John O. Jr Reller, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
Heat-transfer characteristics of blunt two-and three-dimensional bodies at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by Glen Goodwin, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
Approximate solutions for the flow about flat-top wing-body configurations at high supersonic airspeeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1958]), by Raymond C. Savin, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
Effects of overhang balance on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60 degree delta wing at transonic and supersonic speeds /, by Lawrence D. Guy, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Calculation of surface temperatures in steady supersonic flight / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1946), by George P. Wood and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Stability derivatives of triangular wings at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1948), by H. S. Ribner, Frank S. Malvestuto, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
The Calculation of downwash behind supersonic wings with an application to triangular plan forms / (Washington, D.C. : National Advisory Committee for Aeronautics, 1948), by Max A. Heaslet, Harvard Lomax, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Loads on external stores at transonic and supersonic speeds /, by Lawrence D. Guy, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)

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