Aerodynamics, SupersonicSee also what's at your library, or elsewhere.
Broader terms:Narrower terms:- Aerodynamics, Supersonic -- Abstracts
- Aerodynamics, Supersonic -- Air flow
- Aerodynamics, Supersonic -- Bibliography
- Aerodynamics, Supersonic -- Computer programs
- Aerodynamics, Supersonic -- Computer simulation
- Aerodynamics, Supersonic -- Congresses
- Aerodynamics, Supersonic -- Data processing
- Aerodynamics, Supersonic -- History
- Aerodynamics, Supersonic -- Mathematical models
- Aerodynamics, Supersonic -- Measurement
- Aerodynamics, Supersonic -- Research
- Aerodynamics, Supersonic -- Statistical methods
- Aerodynamics, Supersonic -- Statistics
- Aerodynamics, Supersonic -- Tables
- Aerodynamics, Supersonic -- Testing
- Aerodynamics, Hypersonic
- Aerothermodynamics
- Sonic boom
- Supersonic compressors
- Supersonic diffusers
- Supersonic nozzles
- Supersonic planes
- Supersonic wind tunnels
- Air flow -- Aerodynamics, Supersonic
Used for:- Aerodynamics of supersonic flight
- High-speed aerodynamics
- Supersonic aerodynamics
- Supersonic speeds
- Supersonics
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Filed under: Aerodynamics, Supersonic Engineering Supersonic Aerodynamics (New York et al.: McGraw-Hill Book Co., 1950), by Everard Arthur Bonney (page images at HathiTrust) 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) High speed aerodynamics and jet propulsion (Princeton University Press, 1955) (page images at HathiTrust) Elements of aerodynamics of supersonic flows. (Macmillan Co., 1949), by Antonio Ferri (page images at HathiTrust) Linearized theory of conical supersonic flow with application to triangular wings (North American Aviation, Engineering Dept., 1947), by North American Aviation and Wallace D. Hayes (page images at HathiTrust) An investigation of the exact solutions of the linearized equations for the flow past conical bodies (University lithoprinters, 1948), by Otto Laporte, Robert Christian Frank Bartels, and University of Michigan. Office of Research Administration (page images at HathiTrust) Studies on the validity of the hydraulic analogy to supersonic flow (U. S. Air Force, Air Material Command, 1950), 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) Supersonic aerodynamics and rocket propulsion (Los Angeles, 1963), by Robert F. Lee (page images at HathiTrust) Some considerations of sonic boom. ([Washington], 1961), by United States. Federal Aviation Agency. Office of Plans (page images at HathiTrust) Handbook of supersonic aerodynamics. (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) Climatology of the upper air as related to the design and operation of supersonic aircraft (U.S. Dept. of Commerce, Weather Bureau, 1963), by National Weather Records Center (U.S.) and Harold L. Crutcher (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) 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 inlet diffusers and introduction to internal aerodynamics. (Minneapolis-Honeywell Regulator Co., Aeronautical Division, 1956), by Rudolf Hermann (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) Aerodynamics of supersonic flight; an introduction. (Pitman Pub. Corp., 1950), by Alan Pope (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. (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) 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 Air Development Division, Air Research and Development Command., U. S. Air Force, 1958), by Bell Aircraft Corporation and Vincent W. Donato (page images at HathiTrust) A study of finite-difference methods as applied to hypersonic viscous shock-layer equations (Cornell Aeronautical Laboratory, Inc., 1963), by Angela L. Chang and Hsien Kei Cheng (page images at HathiTrust) 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, United States Air Force, 1967., 1967), by Charles R. Strom, Air Force Flight Dynamics Laboratory (U.S.), and Cornell Aeronautical Laboratory (page images at HathiTrust) Lifting surfaces in supersonic flow. (Wright-Patterson air force base, Headquaters, Air materiel command, 1949), by Simon Ostrach and W. H. Pell (page images at HathiTrust; US access only) Three-dimensional inviscid flow about supersonic blunt cones at angle of attack. III, Coupled subsonic and supersonic programs for inviscid three-dimensional flow (Albuquerque, New Mexico : Sandia Corporation, 1968., 1968), 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) Pressure gradient effects on supersonic boundary layer turbulence : final report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979., 1979), by A. J. Laderman, Air Force Flight Dynamics Laboratory (U.S.), and Ford Aerospace & Communications Corporation. Fluid Mechanics Section (page images at HathiTrust) Drag due to lift of a not-so-slender configuration; application of theory. (Cornell Aeronautical Laboratory, Inc., 1958), by Robert J. Vidal (page images at HathiTrust) Reduction of drag due to lift at supersonic speeds (Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1955), by Douglas Aircraft Company and E. W. Graham (page images at HathiTrust) 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) On the hypersonic flow over a delta wing with very supersonic leading edges (Los Angeles, California : North American Aviation Inc., Los Angeles Division, 1965., 1965), by N. Malmuth, United States. Air Force. Office of Scientific Research, and North American Aviation (page images at HathiTrust) 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 (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 (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 Department (page images at HathiTrust) Nonsteady discharge of subcritical flow (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 (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. (U. S. Dept. of Commerce, National Bureau of Standards], 1952), by Robert Ramon Reynolds (page images at HathiTrust) Reverse flow and supersonic interference. (Division of Engineering, Brown University], 1958), by Joseph H. Clarke (page images at HathiTrust) Critical regimes of supersonic jet aircraft; stall and spin (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) Study of lee-side flows over conically cambered delta wings at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Richard M. Wood, Carolyn B. Watson, and Langley Research Center (page images at HathiTrust) Experimental cavity pressure distributions at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1987), by S. Naomi McMillin, Richard M. Wood, and Langley Research Center (page images at HathiTrust) Supersonic aerodynamics of delta wings (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by Richard M. Wood 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Christine M. Darden and Langley Research Center (page images at HathiTrust) Wing planform effects at supersonic speeds for an advanced fighter configuration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Robert L. Stallings, Dana K. Forrest, Floyd J. Wilcox, and Langley Research Center (page images at HathiTrust) Influence of airfoil geometry on delta wing leading-edge vortices and vortex-induced aerodynamics at supersonic speeds (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) Exploratory investigation at mach number of 2.01 of the longitudinal stability and control characteristics of a winged reentry configuration (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 (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 (National Aeronautics and Space Administration, 1966), by Chester H. Wolowicz and United States National Aeronautics and Space Administration (page images at HathiTrust) Longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) Experimental aerodynamic characteristics at Mach numbers from 0.60 to 2.70 of two supersonic cruise fighter configurations (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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) Supersonic wings with significant leading-edge thrust at cruise (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), 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) Transonic aerodynamic damping and oscillatory stability in yaw and pitch for a model of a variable-sweep supersonic transport airplane (National Aeronautics and Space Administration ;, 1966), by Bruce R. Wright, Benjamin T. Averett, and United States National Aeronautics and Space Administration (page images at HathiTrust) Lee-side flow over delta wings at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Peter F. Covell and Langley Research Center (page images at HathiTrust) Supersonic stability and control characteristics of a cruciform missile model with delta wings and aft tail fin controls (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by James C. Townsend 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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) Effect of ratio of wall boundary-layer thickness to jet diameter on mixing of a normal hydrogen jet in a supersonic stream (National Aeronautics and Space Administration ;, 1974), by Charles R. McClinton and Langley Research Center (page images at HathiTrust) Design of a very-low-bleed Mach 2.5 mixed-compression inlet with 45 percent internal contraction (National Aeronautics and Space Administration ;, 1975), by Joseph F. Wasserbauer, Harvey E. Neumann, Robert J. Shaw, and Lewis Research Center (page images at HathiTrust) Estimation of wing nonlinear aerodynamic characteristics at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) Investigation of leading-edge flap performance on delta and double-delta wings at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Cornelius Driver and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust) Aerodynamic characteristics of a supersonic fighter aircraft model at Mach 0.40 to 2.47 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Francis J. Capone, Dorothy Arbiter, E. Ann Bare, and Langley Research Center (page images at HathiTrust) Supersonic longitudinal aerodynamic characteristics of two space shuttle orbiter configurations (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by James C. Ellison and United States National Aeronautics and Space Administration (page images at HathiTrust) Terminal-shock and restart control of a Mach 2.5, axisymmetric, mixed compression inlet with 40 percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Robert J. Baumbick, Robert C. Seidel, Robert E. Wallhagen, and Lewis 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1974), by Raymond E. Gaugler and Lewis Research Center (page images at HathiTrust) Body and canard effects on an attached-flow maneuver wing at Mach 1.62 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration ;, 1974), by Robert J. Baumbick, Carl J. Daniele, Peter G. Batterton, and Lewis Research Center (page images at HathiTrust) NASA TM X-3108 (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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Christine M. Darden and Langley Research Center (page images at HathiTrust) The natural flow wing-design concept (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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1974), by Miles O. Dustin, George H. Neiner, Gary L. Cole, and Lewis Research Center (page images at HathiTrust) Concept development of a Mach 3.0 high-speed civil transport (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) Experimental investigation of a simple distortion index utilizing steady-state and dynamic distortions in a Mach 2.5 mixed-compression inlet and turbofan engine (National Aeronautics and Space Administration ;, 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 (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 (National Aeronautics and Space Administration ;, 1977), by Jerry M. Allen and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA Aerodynamics Program : annual report 1990 (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) Effect of Reynolds number on the aerodynamic stability and control characteristics of a 55 ̊clipped-delta-wing orbiter configuration at supersonic mach numbers (U.S. National Aeronautics and Space Administration ;, 1976), by A. B. Blair, United States National Aeronautics and Space Administration, and Langley Research Center (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 (National Aeronautics and Space Administration ;, 1977), by A. B. Blair and United States National Aeronautics and Space Administration (page images at HathiTrust) Computer program for supersonic kernel-function flutter analysis of thin lifting surfaces (National Aeronautics and Space Administration ;, 1974), by Herbert J. Cunningham and Langley Research Center (page images at HathiTrust) Supersonic aerodynamic characteristics of a series of wrap-around-fin missile configurations (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration ;, 1977), by Barrett L. Shrout 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by William J. Monta and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust) Mechanical characteristics of stability-bleed valves for a supersonic inlet (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Harry W. Carlson, Robert J. Mack, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust) Experimental investigation to validate use of cryogenic temperatures to achieve high Reynolds numbers in boattail pressure testing (U.S. National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1974), by Charles D. Trescot, Dorothy T. Howell, Clarence A. Brown, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Robert L. Stallings, Milton Lamb, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1974), by Robert J. Shaw, Bobby W. Sanders, Glenn A. Mitchell, and Lewis 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 (National Aeronautics and Space Administration ;, 1974), by Glenn A. Mitchell, Robert J. Shaw, Bobby W. Sanders, and Lewis Research Center (page images at HathiTrust) Modification of a three-dimensional supersonic nozzle analysis and comparison with experimental data (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1974), by Warren R. Hingst, Charles E. Towne, and Lewis Research Center (page images at HathiTrust) A method for calculating a real-gas two-dimensional nozzle contour including the effects of gamma (National Aeronautics and Space Administration ;, 1975), by Charles B. Johnson, Lillian R. Boney, and Langley 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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) Theoretical and experimental flow fields for a supersonic cruise fighter forebody (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Steven F. Yaros and Langley Research Center (page images at HathiTrust) Numerical simulation of steady supersonic viscous flow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) A modificiation to linearized theory for prediction of pressure loadings on lifting surfaces at high supersonic Mach numbers and large angles of attack (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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) Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) Evaluation by step response tests of prototype relief valves designed for YF-12 inlet stability bleed system (National Aeronautics and Space Administration ;, 1975), by Miles O. Dustin, George H. Neiner, and Lewis Research Center (page images at HathiTrust) Velocity field of a round jet in a cross flow for various jet injection angles and velocity ratios (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) Effects of spanwise nozzle geometry and location on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1984), 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 (National Aeronautics and Space Administration ;, 1985), by Jeffrey W. Bantle and Langley Research Center (page images at HathiTrust) Experimental investigation of a Mach 5 isentropic spike inlet at and below design speed (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 (National Aeronautics and Space Administration, 1959), by Fred M. Smith and United States National Aeronautics and Space Administration (page images at HathiTrust) Supersonic dynamic-stability derivatives of the space shuttle launch vehicle (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Ajay Kumar, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust) Fluctuating loads measured on an over-the-wing supersonic jet model (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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) Experimental and theoretical supersonic lateral-directional stability characteristics of a simplified wing-body configuration with a series of vertical-tail arrangements (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) The wedge hot-film anemometer in supersonic flow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) The interaction and penetration of gaseous jets in supersonic flow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) A second order slender wing theory for wings with leading edge separation in supersonic flow (National Aeronautics and Space Administration :, 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 (National Aeronautics and Space Administration ;, 1973), by Michael Kenworthy, Joseph A. Schetz, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust) Flow and acoustic characteristics of subsonic and supersonic jets from convergent nozzle (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) Spinning filamentary disk (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) Strong plane shocks in an ideal gas (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) Analytical properties of noise generating mechanisms in a supersonic jet exhaust flow (National Aeronautics and Space Administration ;, 1971), by S. Paul Pao, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust) Fluid entrainment (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) Magnetohydrodynamics during high speed re-entry. (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) A supersonic/hypersonic aerodynamic investigation of the Saturn IB/Apollo upper stage (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 (National Aeronautics and Space Administration, 1966), by Ihor O. Bohachevsky and Robert E. Mates (page images at HathiTrust) Experimental evaluation of a Mach 3.5 axisymmetric inlet (National Aeronautics and Space Administration ;, 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 (U.S. National Aeronautics and Space Administration ;, 1976), by Frank Marconi, Larry Yaeger, United States National Aeronautics and Space Administration, Langley Research Center, and Grumman Aerospace Corporation (page images at HathiTrust) Control of shock wave - boundary layer interactions by bleed in supersonic mixed compression inlets (National Aeronautics and Space Administration ;, 1975), by Michael K. Fukuda, Eli Reshotko, Warren R. Hingst, Lewis Research Center, and Case Western Reserve University (page images at HathiTrust) Effect of interjet spacing on mixing of multiple coaxial jets in supersonic flow (National Aeronautics and Space Administration ;, 1974), by A. K. Lorber, Joseph A. Schetz, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust) A computational system for aerodynamic design and analysis of supersonic aircraft : part 3-computer program description (U.S. National Aeronautics and Space Administration ;, 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) A computational system for aerodynamic design and analysis of supersonic aircraft : part 1-general description and theoretical development (U.S. National Aeronautics and Space Administration ;, 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) Wake analysis for supersonic decelerator applications (National Aeronautics and Space Administration ;, 1970), by Richard A. Lau, Langley Research Center, and Goodyear Aerospace Corporation (page images at HathiTrust) Development and applications of supersonic unsteady consistent aerodynamics for interfering parallel wings (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1973), by J. Syberg, T. E. Hickcox, Ames Research Center, and Boeing Company (page images at HathiTrust) A System for aerodynamic design and analysis of supersonic aircraft. (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) Development of the triplet singularity for the analysis of wings and bodies in supersonic flow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) NASA CR-747 (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) Calculation of three-dimensional, inviscid supersonic, steady flows (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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) Viscous computations of cold air/air flow around scramjet nozzle afterbody (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Oktay Baysal, Walter C. Englelund, Old Dominion University. Dept. of Mechanical Engineering and Mechanics, and Langley Research Center (page images at HathiTrust) Nonparallel instability of supersonic and hypersonic boundary layers (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Nabil M. El-Hady, Langley Research Center, and Inc Analytical Services & Materials (page images at HathiTrust) Study of supersonic wings employing the attainable leading-edge thrust concept (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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) An analytical study of the measured wall pressure field under supersonic turbulent boundary layers (National Aeronautics and Space Administration, 1968), by Thomas J. Black (page images at HathiTrust) Effects of mach number and wall-temperature ratio on turbulent heat transfer at mach numbers from 3 to 5 (U.S. G.P.O.], 1959), by Thorval Tendeland (page images at HathiTrust) Supersonic flow past a family of blunt axisymmetric bodies (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) NASA TR R-311 (National Aeronautics and Space Administration ;, 1969), by Richard W. Barnwell, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only) NASA TR R-368 (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) NASA TR R-374 (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) 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 (National Aeronautics and Space Administration ;, 1975), by Lana M. Couch and Langley Research Center (page images at HathiTrust) Jet effects at supersonic speeds on base and afterbody pressures of a missile model having single and multiple jets (National Aeronautics and Space Administration, 1963), by Nickolai Charczenko, Clyde Hayes, and Langley Research Center (page images at HathiTrust) NASA TN D-2017 (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) Numerical solutions of the Navier-Stokes equations for the supersonic laminar flow over a two-dimensional compression corner (National Aeronautics and Space Administration ;, 1972), by James E. Carter and Langley Research Center (page images at HathiTrust) Some effects of flight path and atmospheric variations on the boom propagated from a supersonic aircraft (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) NASA TR R-164 (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) Static stability and separation characteristics of a two-stage rocket configuration at Mach numbers from 1.57 to 4.50 (National Aeronautics and Space Administration, 1960), by Kenneth L. Turner, Laurence W. Enderson, David S. Shaw, 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 (National Aeronautics and Space Administration ;, 1975), by Lana M. Couch and Langley Research Center (page images at HathiTrust) Supersonic flutter of panels loaded with inplane shear (National Aeronautics and Space Administration ;, 1975), by James Wayne Sawyer and Langely Research Center (page images at HathiTrust) Supersonic longitudinal stability characteristics of the two final stages of a four-stage launch vehicle (National Aeronautics and Space Administration :, 1964), by Royce L. McKinney and Langley Research Center (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 (National Aeronautics and Space Administration ;, 1975), by Donald L. Maiden and Langley Research Center (page images at HathiTrust) Analysis of the dynamic response of a supersonic inlet to flow-field perturbations upstream of the normal shock (National Aeronautics and Space Administration ;, 1975), by Gary L. Cole, Ross G. Willoh, and Lewis Research Center (page images at HathiTrust) NASA TN D-2420 (National Aeronautics and Space Administration :, 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) An experimental investigation of the flow in an axisymmetric internal-compression inlet for M=2.75 (National Aeronautics and Space Administration :, 1961), by Earl C. Watson, William P. Peterson, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-3578 (National Aeronautics and Space Administration :, 1966), by Alan D. Sherer and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Investigation of net-thrust and base-pressure characteristics of cylindrical afterbodies with clustered supersonic nozzles at transonic Mach numbers (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) Turbulence measurements in supersonic, shock-free jets by the optical crossed-beam method (National Aeronautics and Space Administration :, 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 (National Aeronautics and Space Administration, 1961), by Robert W. Cubbison, James J. Ward, Bernhard H. Anderson, and Lewis Research Center (page images at HathiTrust) NASA TN D-5297 (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) NASA TN D-3551 (National Aeronautics and Space Administration :, 1966), by Peter A. Gaspers, Bass Redd, and United States National Aeronautics and Space Administration (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 (National Aeronautics and Space Administration :, 1960), by Warren Gillespie Jr. and Langley Research Center (page images at HathiTrust) NASA TN D-4357 (National Aeronautics and Space Administration ;, 1968), by Robert W. Fralich, John A. McElman, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust) Some divergence characteristics of low-aspect-ratio wings at transonic and supersonic speeds (National Aeronautics and Space Administration :, 1960), by Donald S. Woolston, Herbert J. Cunningham, Frederick W. Gibson, and United States National Aeronautics and Space Administration (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 (National Aeronautics and Space Administration ;, 1974), by Milton Lamb, Robert L. Stallings, and Langley Research Center (page images at HathiTrust) NASA TN D-5816 (National Aeronautics and Space Administration :, 1970), by William D. Deveikis, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) Theoretical face pressure and drag characteristics of forward-facing steps in supersonic turbulent boundary layers (National Aeronautics and Space Administration, 1975), by D. K. Patel and K. R. Czarnecki (page images at HathiTrust) Supersonic dynamic stability characteristics of a space shuttle orbiter (National Aeronautics and Space Administration ;, 1976), by Delma C. Freeman, Edwin E. Davenport, Richmond P. Boyden, and Langley Research Center (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 (National Aeronautics and Space Administration ;, 1971), by Lado Muhlstein, Richard G. Beranek, George C. Marshall Space Flight Center, and Ames Research Center (page images at HathiTrust) Comparisons of theoretical and experimental pressure distributions over a wing-body model at high supersonic speeds (National Aeronautics and Space Administration ;, 1971), by Lloyd S. Jernell, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust) Experimental and numerical investigation of boundary-layer development and transition on the walls of a Mach 5 nozzle (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1975), by S. Z. Pinckney and Langley Research Center (page images at HathiTrust) Mixing of hydrogen injected from multiple injectors normal to a supersonic airstream (National Aeronautics and Space Administration :, 1971), by R. Clayton Rogers, 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 (National Aeronautics and Space Administration ;, 1976), by Michael J. Walsh and Langley Research Center (page images at HathiTrust) Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds (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) Systematic study of error sources in supersonic skin-friction balance measurements (National Aeronautics and Space Administration ;, 1976), by Jerry M. Allen, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust) Investigation of a mixed-compression axisymmetric inlet system at Mach numbers 0.6 to 3.5 (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) Effect of nonlifting empennage surfaces on single-engine afterbody/nozzle drag at Mach numbers from 0.5 to 2.2 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration :, 1960), by C. E. Campbell, J. M. Farley, and Lewis Research Center (page images at HathiTrust) Aerodynamics of a model of the HL-10 flight-test vehicle at Mach 0.35 to 1.80 (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 (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) NASA TN D-5884 (National Aeronautics and Space Administration :, 1970), by C. W. Chiang, Richard D. Wagner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5440 (National Aeronautics and Space Administration ;, 1969), by Wei J. Chyu, Richard D. Hanly, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) A numerical method for evaluation and utilization of supersonic nacelle-wing interference (National Aeronautics and Space Administration :, 1969), by Robert J. Mack, United States National Aeronautics and Space Administration, and Langley 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 (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) NASA TN D-5952 (National Aeronautics and Space Administration :, 1970), by George E. Kaattari, Ames Research Center, and United States National Aeronautics and Space Administration (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 (National Aeronautics and Space Administration ;, 1974), by Robert J. Mack and Langley Research Center (page images at HathiTrust) NASA TN D-5907 (National Aeronautics and Space Administration :, 1970), by Ralph A. Falanga, Edward M. Sullivan, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5338 (National Aeronautics and Space Administration ;, 1969), by Joseph F. Wasserbauer, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5340 (National Aeronautics and Space Administration ;, 1969), by Thomas W. Orange, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5660 (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 (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) NASA TN D-5322 (National Aeronautics and Space Administration ;, 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 (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) NASA TN D-5535 (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) NASA TN D-4719 (National Aeronautics and Space Administration ;, 1968), by James F. Campbell, Dorothy T. Howell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5341 (National Aeronautics and Space Administration ;, 1969), by John V. Rakich, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5359 (National Aeronautics and Space Administration ;, 1969), by Jerald M. Jenkins, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust) A mathematical analysis of supersonic inlet dynamics (National Aeronautics and Space Administration ;, 1968), by Ross G. Willoh, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust) NASA TN D-5717 (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) Application of a 1-strip integral method to the unsteady supersonic aerodynamics of an inclined flat surface (National Aeronautics and Space Administration :, 1972), by Robert M. Bennett, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) Investigation of sonic boom generated by thin, nonlifting, rectangular wings (National Aeronautics and Space Administration ;, 1971), by Sanford S. Davis, Ames 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 (National Aeronautics and Space Administration ;, 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) Heat-transfer measurements at a Mach number of 2 in the turbulent boundary layer on a flat plate having a stepwise temperature distribution (National Aeronautics and Space Administration, 1959), by Raul J. Conti and Langley Research Center (page images at HathiTrust) Experimental heat-transfer distributions on a blunt lifting body at Mach 3.71 (National Aeronautics and Space Administration ;, 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) Jet effects on cylindrical afterbodies housing sonic and supersonic nozzles which exhaust against a supersonic stream at angles of attack from 90 ̊to 180 ̊ (National Aeronautics and Space Administration, 1962), by Lovick O. Hayman, Russell W. McDearmon, 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 (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) Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 (National Aeronautics and Space Administration, 1960), by Charles B. Rumsey, Russell N. Hopko, Robert Owens Piland, and Langley Research Center (page images at HathiTrust) Effects of Mach number on pitot-probe displacment in a turbulent boundary layer (National Aeronautics and Space Administration ;, 1974), by Jerry M. Allen 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 (National Aeronautics and Space Administration :, 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 (National Aeronautics and Space Administration :, 1960), by Arthur Henderson and Langley Research Center (page images at HathiTrust) NASA TN D-6759 (National Aeronautics and Space Administration ;, 1972), by Jerry M. Allen, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) Experimental nozzle expansion and flow characteristics of potassium vapor (National Aeronautics and Space Administration ;, 1966), by Louis J. Goldman, Stanley M. Nosek, and Lewis Research Center (page images at HathiTrust) Calculation of supersonic stream parameters of a real gas from measurable quantities using FORTRAN IV routines (National Aeronautics and Space Administration ;, 1974), by Robert C. Johnson and Lewis Research Center (page images at HathiTrust) A summary of results on sonic-boom pressure-signature variations associated with atmospheric conditions (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) Some effects of mach number and geometry on sonic boom (National Aeronautics and Space Administration ;, 1967), by R. M. Hicks, Lynn W. Hunton, Joel P. Mendoza, and Ames 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 (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 degree half cone at Mach numbers to 0.90 (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 (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 (National Aeronautics and Space Administration, 1961), by William C. Sleeman, A. Warner Robins, and Langley Research Center (page images at HathiTrust) Static thrust augmentation of a rocket-ejector system with a heated supersonic primary jet (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) A method for calculating the aerodynamic loading on wing-body combinations at small angles of attack in supersonic flow (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 (National Aeronautics and Space Administration ;, 1971), by R. C. Shieh, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) A study of methods which predict supersonic flow fields from body geometry, distance, and Mach number (National Aeronautics and Space Administration ;, 1973), by Robert J. Mack 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 (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) Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds (National Aeronautics and Space Administration ;, 1974), by Lloyd S. Jernell and Langley Research Center (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 (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 (National Aeronautics and Space Administration, 1959), by David H. Greenshields and Langley Research Center (page images at HathiTrust) Computer program for calculating the flow field of supersonic ejector nozzles (National Aeronautics and Space Administration ;, 1974), by Bernhard H. Anderson and Lewis Research Center (page images at HathiTrust) NASA TN D-6427 (National Aeronautics and Space Administration ;, 1971), by Larry L. Erickson, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-3932 (National Aeronautics and Space Administration ;, 1967), by Vernard E. Lockwood, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) Concentration measurements of an injected gas in a supersonic stream (National Aeronautics and Space Administration ;, 1967), by Marvin G. Torrence and Langley Research Center (page images at HathiTrust) Unsteady aerodynamic forces on a slender body of revolution in supersonic flow (National Aeronautics and Space Administration, 1961), by Reuben Bond, Barbara B. Packard, and Ames Research Center (page images at HathiTrust) Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions (National Aeronautics and Space Administration ;, 1969), by Helmut F. Butze, Lewis 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 (National Aeronautics and Space Administration :, 1960), by Blake W. Corson, Charles E. Mercer, 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 (National Aeronautics and Space Administration, 1959), by John L. Crigler and Langley Research Center (page images at HathiTrust) NASA TN D-3589 (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) NASA TN D-1600 (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) NASA TN D-1724 (National Aeronautics and Space Administration, 1963), by Terry J. Larson, Lannie D. Webb, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust) Wind-tunnel investigation of paraglider models at supersonic speeds (National Aeronautics and Space Administration, 1961), by Robert T. Taylor and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-1615 (National Aeronautics and Space Administration, 1963), by Robert W. Fralich, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Comparison of experimental and theoretical static aeroelastic loads and deflections of a thin 45° wing in supersonic flow (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) An analysis of nuclear-rocket nozzle cooling (National Aeronautics and Space Administration :, 1960), by William H. Robbins, Arthur A. Medeiros, Daniel Bachkin, and Lewis 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 (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 (National Aeronautics and Space Administration ;, 1971), by Earl R. Keener, Edward J. Hopkins, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust) Flutter of flat rectangular orthotropic panels with biaxial loading and arbitrary flow direction (National Aeronautics and Space Administration :, 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 (National Aeronautics and Space Administration, 1963), by Nickolai Charczenko, Jerry L. Lowery, and Langley Research Center (page images at HathiTrust) NASA TN D-1963 (National Aeronautics and Space Administration, 1963), by Bernard Spencer, W. Pelham Phillips, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Loads induced on a flat plate at a Mach number of 4.5 with a sonic or supersonic jet exhausting normal to the surface (National Aeronautics and Space Administration, 1963), by William Letko 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 (National Aeronautics and Space Administration, 1963), by Lloyd S. Jernell and Langley Research Center (page images at HathiTrust) Pressure measurements of the leading edge of a swept wing at Mach 2.2 (National Aeronautics and Space Administration ;, 1974), by Russell B. Sorrells and Langley Research Center (page images at HathiTrust) Performance of three isentropic all internal compression axisymmetric inlets designed for Mach 2.5 (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 degree (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) Deployment and performance characteristics of 1.5-meter supersonic attached inflatable decelerators (National Aeronautics and Space Administration ;, 1974), by Herman L. Bohon, Robert Miserentino, James Wayne Sawyer, and Langley Research Center (page images at HathiTrust) 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 (National Aeronautics and Space Administration, 1960), by Simon C. Sommer and Ames Research Center (page images at HathiTrust) Experimental and calculated supersonic flutter characteristics of models of the x-15 horizontal and vertical tails (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) Evaluation of compressible-flow Preston tube calibrations (National Aeronautics and Space Administration ;, 1973), by Jerry M. Allen 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 (National Aeronautics and Space Administration ;, 1972), by M. Leroy Spearman, Ida K. Collins, and Langley Research Center (page images at HathiTrust) Correlation of secondary sonic and supersonic gaseous jet penetration into supersonic crossflows (National Aeronautics and Space Administration ;, 1971), by Frederick P. Povinelli, Louis A. Povinelli, and Lewis Research Center (page images at HathiTrust) Effect of diffusers, shrouds, and mass injection on the starting and operating characteristics of a Mach 5 free jet tunnel (National Aeronautics and Space Administration :, 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) The effects of wing-tip droop on the aerodynamic characteristics of a delta-wing aircraft at supersonic speeds (National Aeronautics and Space Administration, 1960), by Richard H. Peterson and Ames Research Center (page images at HathiTrust) Experimental aerodynamic performance characteristics of a rotor entry vehicle configuration : III. Supersonic (National Aeronautics and Space Administration ;, 1971), by Ronald C. Smith, Alan D. Levin, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust) Analytical and experimental performance of optimal controller designs for a supersonic inlet (National Aeronautics and Space Administration ;, 1973), by John R. Zeller and Lewis 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 (National Aeronautics and Space Administration, 1961), by William F. Hinson 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 (National Aeronautics and Space Administration, 1960), by Ross B. Robinson, M. Leroy Spearman, and Langley Research Center (page images at HathiTrust) NASA TN D-2783 (National Aeronautics and Space Administration :, 1965), by Robert E. Fulton, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Numerical methods for the design and analysis of wings at supersonic speeds (National Aeronautics and Space Administration ;, 1974), by Harry W. Carlson, David S. Miller, and Langley Research Center (page images at HathiTrust) NASA TN D-2780 (National Aeronautics and Space Administration :, 1965), by Mamoru Inouye, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) NACA wartime reports (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) NACA wartime reports (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 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 (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 (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 (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 (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 (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 (NACA, 1957), by E. W. Graham and United States National Advisory Committee for Aeronautics (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 (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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration ;, 1975), by Glenn A. Mitchell, Bobby W. Sanders, and Lewis Research Center (page images at HathiTrust) Analytical investigation of fuel temperatures and fuel-evaporation losses encountered in long-range high-altitude supersonic flight (National Advisory Committee for Aeronautics, 1953), by Richard J. McCafferty and Lewis Flight Propulsion Laboratory (page images at HathiTrust) Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99. [Part] 2, Isentropic-spike all-external compression inlet (National Advisory Committee for Aeronautics, 1951), by L. J. Obery, G. W. Englert, 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 (National Advisory Committee for Aeronautics, 1951), by John C. Evvard, John W. Blakey, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Wing tip with subsonic trailing edge (National Advisory Committee for Aeronautics, 1949), by Harold Mirels, James M. Jagger, and Lewis Flight Propulsion Laboratory (page images at HathiTrust) Evaluation of five conical center-body supersonic diffusers at several angles of attack (National Advisory Committee for Aeronautics, 1952), by Gerald W. Englert, Leonard J. Obery, 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 (National Advisory Committee for Aeronautics, 1951), by L. Eugene Baughman, Larence I. Gould, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust) Location of detached shock wave in front of a body moving at supersonic speeds (National Advisory Committee for Aeronautics, 1947), by Edmund V. Laitone and Otway O'M Pardee (page images at HathiTrust) Heat transfer to blunt nose shapes with laminar boundary layers at high supersonic speeds (National Advisory Committee for Aeronautics, 1957), by John O. Reller and Ames Research Center (page images at HathiTrust) Heat-transfer characteristics of blunt 2 and 3 dimensional bodies at supersonic speeds. (National Advisory Committee for Aeronautics, 1956), by Glen Goodwin and Ames Research Center (page images at HathiTrust) Approximate solutions for the flow about flat-top wing-body configurations at high supersonic airspeeds (National Advisory Committee for Aeronautics, 1958), by Raymond C. Savin and Ames Research Center (page images at HathiTrust) Application of oblique-shock sensing system to ram-jet-engine flight Mach number control (National Aeronautics and Space Administration, 1955), by Fred A. Wilcox, Donald P. Hearth, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Aeronautics and Space Administration (page images at HathiTrust) Combustion of aluminum borohydride in a supersonic wind tunnel (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, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Preliminary attempts at isothermal compression of a supersonic air stream (National Advisory Committee for Aeronautics, 1956), by E. Perchonok, F. Wilcox, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1956), by Donald P. Hearth, Robert W. Cubbison, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1956), by Andrew Beke, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1956), by Thomas G. Piercy, Bruce G. Chiccine, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Design and experimental performance of standard turbine (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, 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 (National Advisory Committee for Aeronautics, 1958), by J. Cary Nettles, Robert C. Campbell, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Airplane motions and loads induced by flying through the flow field generated by an airplane at low supersonic speeds (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, 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 (National Advisory Committee for Aeronautics, 1956), by Fred A. Wilcox, Paul Whalen, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1949), by Eugene S. Love, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1950), by John D. Morrow, Ellis Katz, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1952), by Joseph M. Hallissy, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) Longitudinal aerodynamic characteristics of a model airplane configuration equipped with a scaled X-1 airplane wing (National Advisory Committee for Aeronautics, 1952), by James H. Parks, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) Pressure distribution measurements of the interference effect of the wing on the fuselage at mach numbers of 1.40 and 1.59 (National Advisory Committee for Aeronautics, 1952), by John P. Gapcynski, United States. National Adviosry Committee for Aeronautics, Langley Aeronautical Laboratory, and James W. Clark (page images at HathiTrust) Effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch at M = 2.0 (National Advisory Committee for Aeronautics, 1952), by Ross B. Robinson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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 (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 (page images at HathiTrust) The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow (National Advisory Committee for Aeronautics, 1952), by Eugene S. Love, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) Investigations at supersonic speeds of the base pressure on bodies of revolution with and without sweptback stabilizing fins (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 (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 (National Advisory Committee for Aeronautics, 1952), by Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) Average skin-friction coefficients from boundary-layer measurements on an ogive-cylinder body in flight at supersonic speeds (National Advisory Committee for Aeronautics, 1953), by J. Dan Loposer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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 (National Advisory Committee for Aeronautics, 1953), by Harvey A. Wallskog, Roger G. Hart, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) A combined aerodynamic and guidance approach for a simple homing system (National Advisory Committee for Aeronautics, 1953), by Robert A. Gardiner, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) Factors affecting transition at supersonic speeds (National Advisory Committee for Aeronautics, 1953), by K. R. Czarnecki, Archibald R. Sinclair, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1953), by August F. Bromm, Julia M. Goodwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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 (National Advisory Committee for Aeronautics, 1958), by Sumner A. Leadbetter, Sherman A. Clevenson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1954), by Joseph R. Milillo, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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 (National Advisory Committee for Aeronautics, 1954), by Mitchel H. Bertram, William D. McCauley, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) A method for designing low-drag nose-inlet-body combinations for operation at moderate supersonic speeds (National Advisory Committee for Aeronautics, 1954), by Robert R. Howell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 (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, 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 (National Advisory Committee for Aeronautics, 1955), by Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry 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 (National Advisory Committee for Aeronautics, 1955), by Charles B. Rumsey, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Factors affecting the maximum lift-drag ratio at high supersonic speeds (National Advisory Committee for Aeronautics, 1956), by Charles H. McLellan, Robert W. Dunning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Span loadings due to wing twist at transonic and supersonic speeds (National Advisory Committee for Aeronautics, 1957), by Frederick C. Grant, John P. Mugler, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1957), by John A. Moore, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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 (National Advisory Committee for Aeronautics, 1958), by Robert R. Howell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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 (National Advisory Committee for Aeronautics, 1958), by Abraham Leiss, Walter J. Kouyoumjian, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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. (National Advisory Committee for Aeronautics, 1958), by Alan B. Kehlet, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust) Some effects of fin plan form on the static stability of fin-body combinations at Mach number 4.06 (National Advisory Committee for Aeronautics, 1952), by Edward F. Ulmann, Robert W. Dunning, Langley Aeronautical Laboratory, and United States. National Adviosry 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 (National Advisory Committee for Aeronautics, 1953), by Paul G. Fournier, Andrew L. Byrnes, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) The static and dynamic longitudinal stability characteristics of some supersonic aircraft configurations (National Advisory Committee for Aeronautics, 1952), by Jesse L. Mitchell, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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 (National Advisory Committee for Aeronautics, 1954), by Ernest C. Seaberg, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust) Performance of external-compression bump inlet at Mach numbers of 1.5 to 2.0 (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 (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 (National Advisory Committee for Aeronautics, 1957), by Reginald R. Lundstrom, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Theoretical study of air forces on an oscillating or steady thin wing in a supersonic main stream (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 (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 (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 (National Advisory Committee for Aeronautics, 1949), by Arthur L. Jones, Alberta Alksne, 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 (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) Effect of aspect ratio on undamped torsional oscillations of a thin rectangular wing in supersonic flow (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 (National Advisory Committee for Aeronautics, 1949), by James C. Livengood and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Line-vortex theory for calculation of supersonic downwash (National Advisory Committee for Aeronautics, 1949), by Harold Mirels, Rudolph C. Haefeli, 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 (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 (National Advisory Committee for Aeronautics, 1949), by Clinton E. Brown 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 (National Advisory Committee for Aeronautics, 1949), by William R. Wimbrow 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 (National Advisory Committee for Aeronautics, 1949), by Doris Cohen 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 (National Advisory Committee for Aeronautics, 1951), by Seymour Lampert 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 (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 (National Advisory Committee for Aeronautics, 1951), by Maurice Tucker, Stephen H. Maslen, 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 (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) Applications of Von Karman's integral method in supersonic wing theory (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 (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 (National Advisory Committee for Aeronautics, 1951), by Robert O. Piland and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Axisymmetric supersonic flow in rotating impellers (National Advisory Committee for Aeronautics, 1951), by Arthur W. Goldstein 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 (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 (National Advisory Committee for Aeronautics, 1955), by Benjamin H. Beam and United States National Advisory Committee for Aeronautics (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 (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) Transonic aerodynamic characteristics of a model of a proposed six-engine hull-type seaplane designed for supersonic flight (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 (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 (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° (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 (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) The stabilizing effectiveness of conical flares on bodies with conical noses (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) 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 (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) Stability and control characteristics at a mach number of 2.01 of a supersonic VTOL airplane model having a broad fuselage and small delta wings (National Aeronautics and Space Administration, 1961), by Cornelius Driver, M. Leroy Spearman, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Skin and structural temperatures measured on the X-15 airplane during a flight to a mach number of 3.3 (National Aeronautics and Space Administration, 1961), by Robert D. Reed, Joe D. Watts, and Flight Research Center (U.S.) (page images at HathiTrust; US access only) Effect of vertical-tail modifications on the static stability characteristics at mach number of 2.2 of a supersonic vtol airplane model having a broad fuselage and small delta wings (National Aeronautics and Space Administration, 1961), by Ross B. Robinson, Leroy M. Spearman, and Langley Research Center (page images at HathiTrust; US access only) Free-flight measurements of static and dynamic stability of models of the Project Mercury re-entry capsule at Mach numbers 3 and 9.5 (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 (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 (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) Static stability and control characteristics of an airplane model with tail surfaces outboard of the wing tips at a mach number of 2.01 (National Aeronautics and Space Administration, 1959), by Cornelius Driver, M. Leroy Spearman, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Experimental and calculated results of a flutter investigation of some very low aspect-ratio flat-plate surfaces at Mach numbers from 0.62 to 3.00 (National Aeronautics and Space Administration, 1959), by Perry W. Hanson, Gilbert M. Levey, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) 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 (National Aeronautics and Space Administration, 1960), by John P. Gapcynski and United States National Aeronautics and Space Administration (page images at HathiTrust) Free-flight investigation at supersonic speeds of the stability and drag of a 79° clipped delta boost-glide configuration including an analog study of coupled motions during the flight (National Aeronautics and Space Administration, 1961), by Sherwood Hoffman, Willard S. Blanchard, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Performance of a Mach Number 3.0 design axisymmetric double-cone external-compression inlet in the mach number range 1.97 to 0.79 (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 (National Aeronautics and Space Administration, 1960), by John R. Sevier and United States National Aeronautics and Space Administration (page images at HathiTrust) Some effects of aircraft configuration on static longitudinal and directional stability characteristics at supersonic Mach numbers below 3 (National Advisory Committee for Aeronautics, 1959), by M. Leroy Spearman, Arthur Henderson, 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 (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 (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 (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 (National Advisory Committee for Aeronautics, 1958), by Nick E. Samanich, Robert W. Cubbison, and United States. National Adviosry Committee for Aeronautics (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 (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 (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 (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) Supersonic parachute test vehicle ([National Technical Information Service], 1960), by M.T. Kane, B. L. Barth, and Sandia Corporation (page images at HathiTrust) Compilation and correlation of model starting loads from several supersonic wind tunnels ([Sandia Corporation], 1962), by R. C. Maydew, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust) Flow over a slender body of revolution at supersonic velocities (National Advisory Committee for Aeronautics, 1946), by Robert T. Jones, Kenneth Margolis, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Calculation of surface temperatures in steady supersonic flight (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 (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) A Method for determining the aerodynamic characteristics of two- and three-dimensional shapes at hypersonic speeds (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) The Calculation of downwash behind supersonic wings with an application to triangular plan forms (National Advisory Committee for Aeronautics, 1948), by Max A. Heaslet, Harvard Lomax, 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 (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) Characteristics of a free supersonic helium jet issuing normally from a flat plate (Sandia Corporation ;, 1960), by A. Bedford and Sandia Corporation (page images at HathiTrust) High-speed computing machine calculation of supersonic axisymmetric flows (Aberdeen, Maryland : Aberdeen Proving Ground, 1954., 1954), 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 (Aberdeen Proving Ground, Maryland : Ballistic Research Laboratories, 1973., 1973), by Robert L. McCoy and U.S. Army Ballistic Research Laboratory (page images at HathiTrust) Expansion of tables II and III of National Adviosry Committee for Aeronautics technical note no. 1428 (Aberdeen Proving Ground, Maryland : Ballistic Research Laboratories, 1951., 1951), by U.S. Army Ballistic Research Laboratory (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 (Washington, D.C. : National Advisory Committee for Aeronautics, 1954., 1954), by Lawrence D. Guy, Langley Aeronautical Laboratory, 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 (Washington, D.C. : National Advisory Committee for Aeronautics, 1954., 1954), by Alan B. Kehlet, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Loads on external stores at transonic and supersonic speeds (Washington, D.C. : National Advisory Committee for Aeronautics, 1955., 1955), by Lawrence D. Guy, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust) Comparative flutter calculations on low-aspect-ratio wings in incompressible and supersonic flows. (M.I.T. Department of Aeronautical Engineering, 1954), by Garabed Zartarian, Herbert M. Voss, and Pao Tan Hsu (page images at HathiTrust) Control of supersonic aircraft. (Wright-Patterson Air Force Base, Ohio, 1966), by Feliko Iosifovich Sklianskii (page images at HathiTrust) Measurement of recovery factors and friction coefficients for supersonic flow of air in a tube. [Part] II. Results based on a two-dimensional flow model for entrance region (Cambridge, Massachusetts : Massachusetts Institute of Technology, Division of Industrial Cooperation, 1951., 1951), 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) On harmonic motion of wide delta airfoils at supersonic speeds (U.S. Naval Ordnance Test Station, Research Dept., Ballistics Division, Aerodynamics Branch, 1950), by John Miles (page images at HathiTrust) The drag of a delta wing in supersonic flow (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) Methods for conducting short-time tensile, creep, and creep-rupture tests under conditions of rapid heating (Columbus, Ohio : Defense Metals Information Center, Battelle Memorial Institute, 1959., 1959), by Donald P. Moon, Ward F. Simmons, Defense Metals Information Center (U.S.), 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 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), 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 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), 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 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), by William Joseph Yanta and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust) Supersonic magnus measurements of the 10-Caliber Army-Navy spinner projectile with wrap-around fins (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), by Frank J. Regan, Virginia L. Schermerhorn, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust) The use of a laser doppler velocimeter in supersonic flow (White Oak, Maryland : United States Naval Ordnance Laboratory, 1971., 1971), by William Joseph Yanta, Francis W. Brown, David F. Gates, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust) Unsteady supersonic flow (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) Numerical technique for the three-dimensional blunt-body problem (Albuquerque, New Mexico : Sandia Corporation, 1968., 1968), by G. Moretti, G. Bleich, U.S. Atomic Energy Commission, Nassau County General Applied Science Laboratories (Westbury, and Sandia Corporation (page images at HathiTrust) Numerical technique for the three-dimensional blunt-body problem (Albuquerque, New Mexico : Sandia Corporation, 1968., 1968), by G. Moretti, U.S. Atomic Energy Commission, Nassau County General Applied Science Laboratories (Westbury, and Sandia Corporation (page images at HathiTrust) Surface flow angles on an ogive cylinder at angle of attack in supersonic flow (Albuquerque, New Mexico : Sandia Laboratories, 1971., 1971), by Harold R. Vaughn, Oscar L. George, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust) A theory for base pressures in transonic and supersonic flow (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) A theory for base pressures in transonic and supersonic flow (Mechanical Engineering Dept., Univ. of Illinois, 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) Compressible two-dimensional jet mixing at constant pressure : tables of auxiliary functions for fully developed mixing profiles (Mechanical Engineering Dept., University 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) Truncated cone in supersonic flight at zero angle of attack : surface pressure coefficients, drag coefficients, and shock front configurations (Mechanical Engineering Dept., Engineering Experiment Station, University of Illinois, 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) A Program for computing steady inviscid three-dimensional supersonic flow on reentry vehicles : volume I : analysis and programming (Silver Spring, Maryland : Naval Surface Weapons Center, White Oak Laboratory, 1977., 1977), 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) an Investigation of the use of holography in studying supersonic flow in inlets. (Silver Spring, Maryland : Naval Ordnance Laboratory, White Oak, 1973., 1973), by III Spring, W. C. Ragsdale, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust) Sonic limit singularities: Part II: Examples (College Park, Maryland : University of Maryland, Institute for Fluid Dynamics and Applied Mathematics, 1958., 1958), 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) Sonic limit singularities: Part I: General theory (College Park, Maryland : University of Maryland, Institute for Fluid Dynamics and Applied Mathematics, 1958., 1958), 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) Survey of boundary layer heat transfer at high velocities and high temperatures (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1960., 1960), by E. R. G. Eckert, United States. Air Force. Air Research and Development Command, Wright Air Development Center, University of Minnesota, and United States. Department of the Air Force. 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 (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1954, 1954), by Lloyd E. Daniels, H. Yoshihara, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust) Survey on heat transfer at high speeds (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1954, 1954), by E. R. G. Eckert, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust) Supersonic flutter trends as revealed by piston theory calculations (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Holt Ashley, Garabed Zartarian, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust) Supersonic wind tunnel tests of ring-wing configurations (Wright-Patterson Air Force Base, Ohio, Wright Air Development Division, Air Research and Development Command., United States Air Force, 1958., 1958), by Leon H. Schindel, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust) Supersonic panel flutter (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1957., 1957), by Yudell L. Luke, Andrew St. John, United States. Air Force. Air Research and Development Command, 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 (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1957., 1957), by Yudell L. Luke, Frank Wagner, Geraldine V. Coombs, United States. Air Force. Air Research and Development Command, Midwest Research Institute, and 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 (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1957., 1957), by Antonio Ferri, Paul A. Libby, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Aerospace Research Laboratories (U.S.) (page images at HathiTrust) Supersonic mixing of jets and turbulent boundary layers (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1957., 1957), by Harry E. Bailey, Arnold M. Kuethe, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust) Estimation of damping in roll of wings at high supersonic speeds ... ([Princeton, 1948), by Edward Seckel (page images at HathiTrust) Handbook of supersonic aerodynamics. (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) Inhibition of flow separation at high speed. Volume 1, Supersonic turbulent boundary layers (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by Larry L. Lynes, Frederick K. Goodwin, Jack Norman Nielsen, Air Force Flight Dynamics Laboratory (U.S.), and Nielsen Engineering & Research (page images at HathiTrust) Mach 0.6 to 3.0 flows over rectangular cavities (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1983., 1983), by Louis G. Kaufman, Rodney L. Clark, Algirdas Maciulaitis, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aerospace Corporation. Research and Development Center (page images at HathiTrust) Computer program for design and/or analysis of two-dimensional and axisymmetric inlets (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979., 1979), by Larry K. Ratliff and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust) Summary of laminar boundary layer control research (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1964., 1964), by Northrop Corporation. Boundary Layer Research Section and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust) Analytical and experimental investigation of supersonic parachute phenomena (Wright-Patterson Air Force Base, Ohio : Flight Accessories Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by L. W. Sims and 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 (Wright-Patterson Air Force Base, Ohio : Deputy for Engineering, Aeronautical Systems Division, Air Force Systems Command, 1968., 1968), by Donald A. Watne and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust) High speed smoke flow visualization (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by Stephen M. Batill, T. J. Mueller, Robert C. Nelson, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and University of Notre Dame. Department of Aerospace and Mechanical Engineering (page images at HathiTrust) Supersonic flow about general three-dimensional blunt bodies. Volume II, Heat transfer due to the interaction between a swept planar shock wave and a Laminar boundary layer (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by A. Martellucci, Paul A. Libby, Nassau County General Applied Science Laboratories (Westbury, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust) Evaluation of USSAERO and HABP computer codes for aerodynamic predictions for slender bodies (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by Jack I. Flaherty, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust) Uniqueness of solution of the problem of supersonic flow past a wedge (Graduate Division of Applied Mathematics, Brown University, 1948), by F. I. Frankl (page images at HathiTrust) Blowing from a porous cone or wedge when the contact surface is straight (Los Angeles, California : Space Systems and Ballistic Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1966., 1966), by George Emanuel, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust) Force tests of standard hypervelocity ballistic models HB-1 and HB-2 at Mach 1.5 to 10 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by J. Don Gray, E. Earl Lindsay, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) Investigation of the effects of nose bluntness on natural and induced boundary-layer transition on axisymmetric bodies in supersonic flow (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by Jack D. Coats, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) Stability of boundary layers at high supersonic and hypersonic speeds (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1991., 1991), by T. Herbert, Ohio State University. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust) Investigation of the physics of screech in supersonic jets and turbulent boundary layers at high Reynolds number and control of separation through oscillatory blowing (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1996., 1996), by Hassan M. Nagib, Michael Hites, I. Wygnanski, Ahmed Naguib, Candace Wark, United States. Air Force. Office of Scientific Research, and Illinois Institute of Technology (page images at HathiTrust) Handbook of supersonic aerodynamics : Section 15, Properties of gases (Washington, D.C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory, 1953., 1953), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) Turbulent boundary layer characteristics at high Reynolds number (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by V. Zakkay, Aerospace Research Laboratories (U.S.), and New York University. Aerospace and Energetics Laboratory (page images at HathiTrust) Flow visualization photographs of a yawed tangent ogive cylinder at Mach number 2 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by J. H. Jones, J. E. O'Hare, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust) Thrust augmentation study of high performance ejectors (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1983, 1983), by John E. Minardi, Hans von Ohain, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and University of Dayton. Research Institute (page images at HathiTrust) Singularities at the sonic velocity (Project No. HA-219) (Wright-Patterson Air Force Base, Dayton, Ohio : Headquarters, Air Materiel Command, 1948, 1948), by Karl Gottfried Guderley and United States. Army Air Forces. Air Matériel Command (page images at HathiTrust) Dominance of radiated aerodynamic noise on boundary-layer transition in supersonic-hypersonic wind tunnels : theory and application (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by Samuel R. Pate, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Handbook of supersonic aerodynamics : Volume 4 (Washington, D. C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory , 1952., 1952), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) Considerations on the structure of mixed subsonic-supersonic flow patterns (Wright Field, Dayton, Ohio : Headquarters Air Materiel Command, 1947., 1947), by Karl Gottfried Guderley and United States. Army Air Forces. Air Matériel Command (page images at HathiTrust) Handbook of supersonic aerodynamics : Section 18, Shock tubes (Washington, D.C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory, 1959., 1959), by I. I. Glass, J. Gordon Hall, University of Toronto. Institute of Aerophysics, Johns Hopkins University. Applied Physics Laboratory, and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) A note on the pressure disturbance at ground level caused by high-flying supersonic aircraft ([Washington, D.C.] : [United States Air Force, Office of Scientific Research], [1958], 1958), by N. C. Freeman, S. H. Lam, United States. Air Force. Office of Scientific Research, and Princeton University. Department of Aeronautical Engineering (page images at HathiTrust) Study to determine aerodynamic characteristics on hypersonic re-entry configurations. Part II--Analytical Phase, Volume 2--Design Charts (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1962., 1962), by Frank S. Malvestuto, Vivan E. Huggins, Jules A. Larrivee, Herbert A. Mortzschky, William L. Marcy, Phillip J. Sullivan, Lockheed Aircraft Corporation, United States. Air Force. Systems Command. Aeronautical Systems Division, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust) Survey of CFD applications for high speed inlets (Wright Patterson Air Force Base, Ohio : Flight Dynamics Directorate , Wright Laboratory, Air Force Materiel Command, United States Air Force, 1994., 1994), by Keith E. Numbers and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust) Characterization of the flowfield near a wrap-around fin at supersonic speeds (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 1998., 1998), by Carl P. Tilmann and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust) Comparative experimental and theoretical studies of the flutter of flat panels in a low supersonic flow (Washington, D.C. : United States Air Force, Office of Scientific Research, 1961., 1961), by M. H. Lock, Y. C. Fung, United States. Air Force. Office of Scientific Research, and California Institute of Technology (page images at HathiTrust) Analytical nodel of supersonic, turbulent, near-wake flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by C. E. Peters, W. J. Phares, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Laser velocimetry measurements of vortex flows on a delta wing at Mach 1.9 (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate , Wright Laboratory, Air Force Materiel Command, United States Air Force, 1993., 1993), by Linda G. Smith, C. Dean Miller, George L. Seibert, Charles Tyler, Mark S. Maurice, and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust) Wind tunnel tests of two-dimensional and half-axisymmetric inlet models at Mach numbers 1.5 through 3.0 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1970., 1970), by Frederick K. Hube, Leroy M. Jenke, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) A comparison of transition Reynolds numbers from 12-in. and 40-in. supersonic tunnels (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by C. J. Schueler, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) Massive blowing experiments (Los Angeles, California : Space Systems and Ballistic Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1967., 1967), by Jerry F. Bott, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust) Supersonic aerodynamic characteristics of the Active Laser Seeker (ALS) configuration of a proposed maneuvering air-to-air missile design (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by D. H. Fikes, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Analysis of laminar boundary layers on right circular cones at angle of attack, including streamline-swallowing effects (Arnold Air Force Station, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, 1972., 1972), by Arloe Wesley Mayne, Inc ARO, and Arnold Engineering Development Center (page images at HathiTrust) Low Reynolds number aerodynamics of flapped airfoils at supersonic speeds (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by James L. Amick, Gerard F. Carvalho, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and University of Michigan (page images at HathiTrust) Two-dimensional airfoils (Washington, D. C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory , 1957., 1957), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) Aerodynamic interference of two axisymmetric stores at low supersonic speeds (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armamanet Development and Test Center, Air Force Systems Command, United States Air Force, 1976., 1976), by John E. Burkhalter, Fred W. Martin, United States. Air Force. Systems Command, Air Force Armament Laboratory, and Auburn University. Department of Aerospace Engineering (page images at HathiTrust) Handbook of supersonic aerodynamics : Volume 1 (Washington, D. C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory , 1950., 1950), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) Pressure distribution tests of several sharp leading edge wings, bodies, and body-wing combinations at Mach 5 and 8 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Research and Development Command, United States Air Force, 1960., 1960), by R. E. Randall, J. L. Burk, D. R. Bell, Inc ARO, United States. Air Force. Air Research and Development Command, and Arnold Engineering Development Center (page images at HathiTrust) Analysis of the three-dimensional compressible turbulent boundary layer on a sharp cone at incidence in supersonic and hypersonic flow (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by John C. Adams, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) A method of characteristics computer program for three-dimensional supersonic internal flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1979., 1979), by W. C. Armstrong, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Aerodynamic test and analysis of a slender generic missile configuration (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Aeromechanics Division, Air Force Systems Command, United States Air Force, 1989., 1989), by Roger S. Gates, Mark A. Fische, John R. Cipolla, G. L. Winchenback, United States. Air Force. Systems Command, and Air Force Armament Laboratory (page images at HathiTrust) Viscous flow interaction studies : final report on work unit 7064 02 06 (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by Robert H. Korkegi and Aerospace Research Laboratories (U.S.) (page images at HathiTrust) Investigation of boundary-layer suction on a 20-caliber Ogive cylinder at Mach numbers 2.5, 3.0, 3.5, and 4.0 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1961., 1961), by W. T. Strike, S. Pate, Inc ARO, United States. Air Force. Air Research and Development Command, and Arnold Engineering Development Center (page images at HathiTrust) Wind tunnel and full-scale forces on rocket sleds (Holloman Air Force Base, New Mexico : Air Force Missile Development Center, Air Force Systems Command, 1967., 1967), by Daniel J. Krupovage, Otto T. Pokorny, Larry C. Mixon, and Air Force Missile Development Center (U.S.) (page images at HathiTrust) Research on supersonic turbulent separated and reattached flows (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by Seymour M. Bogdonoff, G. Simpers, G. S. Settles, Irwin E. Vas, Aerospace Research Laboratories (U.S.), and Princeton University. Gas Dynamics Laboratory (page images at HathiTrust) The AFFDL-Nielsen flow-field study (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by William T Strike, John H. Porter, Terry R. Penney, Nielsen Engineering & Research, Air Force Flight Dynamics Laboratory (U.S.), Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust) Inlet performance characteristics of a generalized 1/5.2-scale aircraft model at transonic and supersonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by Jimmy Walker, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Boundary layer transition at supersonic speeds : three dimensional roughness effects (spheres) (Washington, D.C. : Air Force Office of Scientific Research, United States Air Force, 1961., 1961), by E. R. Van Driest, C. B. Blumer, United States. Air Force. Office of Scientific Research, and North American Aviation. Space and Information Systems Division (page images at HathiTrust) Supersonic near free molecule flow over a specularly reflecting flat plate with a deflected flap (Los Angeles, California : Space Systems and Ballistic Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1966., 1966), by Charles R. Ortloff, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust) A study of penetration of a liquid injectant into a supersonic flow (Los Angeles, California : Space and Missile Systems Organization, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1967., 1967), by Kenneth P. Horn, Roy E. Reichenbach, Marc A. Kolpin, United States. Air Force. Systems Command, Space and Missile Systems Organization (U.S.), and Aerospace Corporation (page images at HathiTrust) Support for graduate research in supersonic reacting flows (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, 1998., 1998), by Mark Godfrey Mungal, Stanford University. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust) Investigation of drag reduction by boundary-layer suction on a flat plate and a 36-deg swept wing at supersonic speeds (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1962., 1962), by S. R. Pate, J. S. Deitering, Inc. AEDC Division Sverdrup/ARO, and Arnold Engineering Development Center (page images at HathiTrust) Wave evolution and laminar-turbulent transition in fully 3D supersonic flows (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1996., 1996), by T. Herbert and United States. Air Force. Office of Scientific Research (page images at HathiTrust) Sinusoidal variation ([Washington, D.C.] : [United States Air Force, Office of Scientific Research], [1960], 1960), by Maurice Holt, Bohyun Yim, United States. Air Force. Office of Scientific Research, and Brown University. Division of Applied Mathematics (page images at HathiTrust) Linear variation ([Washington, D.C.] : [United States Air Force, Office of Scientific Research], [1960], 1960), by Maurice Holt, Bohyun Yim, United States. Air Force. Office of Scientific Research, and Brown University. Division of Applied Mathematics (page images at HathiTrust) The use of shaped cavities to improve the sidewall boundary layer quality in gas dynamic lasers (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by James S. Petty, Robert H. Korkegi, James R. Cooper, Aerospace Research Laboratories (U.S.), and United States. Air Force. Office of Aerospace Research (page images at HathiTrust) Static aerodynamic characteristics of a series of generalized slender bodies with and without fins at Mach numbers form 0.6 to 3.0 and angles of attack from 0 to 180 deg. Volume 1 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by William B. Baker, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust) Calibration tests of a Litton conical air data probe at Mach numbers of 2 to 8 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1962., 1962), by Scott R. Mallard, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) The flutter of two-bay flat panels of infinite span at supersonic Mach numbers (Los Angeles, California : Ballistic Systems and Space Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1964., 1964), by M. H. Lock, Edith F. Farkas, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation. Laboratory Operations (page images at HathiTrust) An application of the Chapman-Korst theory to supersonic nozzle-afterbody flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by R. C. Bauer, J. H. Fox, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Computations of supersonic vortical flows around ogive-cylinders using central and upwind differences (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Materiel Command, United States Air Force, 1997., 1997), by Eswar Josyula and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust) Inlet performance characteristics of a generalized 1/4-scale tactical aircraft models at transonic and supersonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1971., 1971), by R. F. Lauer, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Supersonic flow measurements in the body vortex wake of an ogive nose cylinder (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Development and Test Center, Air Force Systems Command, United States Air Force, 1978., 1978), by William L. Oberkampf, T. J. Bartel, United States. Air Force. Systems Command, and Air Force Armament Laboratory (page images at HathiTrust) Analysis of three-dimensional inviscid supersonic flow between a body and an outer wall : with application to a jet stretcher system (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by W. C. Armstrong, R. C. Bauer, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust) Handbook of supersonic aerodynamics : Section 17, Ducts, nozzles and diffusers (Washington, D.C. : U.S. Bureau of Naval Weapons, U.S. Naval Ordnance Laboratory, 1964., 1964), by George Rudinger, Johns Hopkins University. Applied Physics Laboratory, and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) High-fidelity multidisciplinary design using an integrated design environment (Arlington, Virginia. : Air Force Office of Scientific Research, 2007., 2007), by Antony Jameson, Stanford University. Department of Aeronautics and Astronautics, and United States. Air Force. Office of Scientific Research (page images at HathiTrust) Finite-difference solution of the laminar supersonic near wake : a posteriori error study and physical discussion (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1974., 1974), by Bruce B. Ross, Sin-I Cheng, Aerospace Research Laboratories (U.S.), and Princeton University. Gas Dynamics Laboratory (page images at HathiTrust) Wind tunnel tests of supersonic two-dimensional and half-axisymmetric inlet models in a nonuniform flow field at Mach numbers from 1.5 through 2.5 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1971., 1971), by Frederick K. Hube, Leroy M. Jenke, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) Handbook of supersonic aerodynamics : Volume 2 / Johns Hopkins University, Applied Physics Laboratory. (White Oak, Maryland : U.S. Naval Ordnance Laboratory, 1950), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) Aerodynamics of supersonic lifting bodies (Air Force Armament Laboratory, Armamaent Division, Air Force Systems Command, United States Air Force, 1981), by M. C. Jischke, M. L. Rasmussen, United States. Air Force. Systems Command, Air Force Armament Laboratory, and Mechanical University of Oklahoma. School of Aerospace (page images at HathiTrust) Wind tunnel investigation of a spike-bluff body combination for a monorail rocket sled M = 2.0 to M = 5.0 (Holloman Air Force Base, New Mexico : Air Force Office of Scientific Research, Directorate of Research Analyses, United States Air Force, 1962., 1962), by Rudolf Hermann, Donald Olson, Frederick Moynihan, United States. Air Force. Office of Scientific Research, Rosemount Aeronautical Laboratories, and University of Minnesota. Institute of Technology (page images at HathiTrust) Study of compressible flow through a rectangular-to-semiannular transition duct (National Aeronautics and Space Administration, Scientific and Technical Information Program, 1995), by Jeffry Foster and Lewis Research Center (page images at HathiTrust) Theoretical analysis of the flow field over a family of ogive bodies (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Aeroballistics Directorate, 1977., 1977), by Ronnie W. Guy, Redstone Arsenal (Ala.), United States. Army. Missile Command, and inc Science Applications (page images at HathiTrust) Procedures for estimating inlet external and internal performance (China Lake, California : Naval Weapons Center, Propulsion Development Department, 1974., 1974), by B. M. Sharp, J. P. Howe, McDonnell Aircraft Company, and Naval Weapons Center (page images at HathiTrust) Supersonic inlet investigation. Volume I, Summary report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by T. W. Tsukahira, Gordon R. Hall, M. Yaamada, W. F. Wong, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust) Handbook of supersonic aerodynamics. Section 17, Ducts, nozzles and diffusers (Silver Spring, Maryland : The Johns Hopkins University, Applied Physics Laboratory, 1964., 1964), by George Rudinger, Johns Hopkins University. Applied Physics Laboratory, and United States Bureau of Naval Weapons (page images at HathiTrust) Supersonic inlet investigation. Volume III, Wind tunnel data report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by T. W. Tsukahira, B. G. Franco, W. F. Wong, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust) Supersonic inlet investigation. Volume II, Air induction sysem dynamic simulation model (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by Nasim F. Amin, Gordon R. Hall, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust) An oil flow study of a sonic reaction jet ejecting from a body of revolution into a free stream of Mach number range 1.75 to 4.5 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Labortory, 1970., 1970), by Troy A. Street, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust) Handbook of supersonic aerodynamics : Section 18, Shock tubes (Washington, D.C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory, 1959., 1959), by I. I. Glass, J. Gordon Hall, Johns Hopkins University. Applied Physics Laboratory, and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) Prediction of unsteady aerodynamic loadings on non-planar wings and wing-tail configurations in supersonic flow. Part II, Computer program description (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1972., 1972), by Gordon D. Kramer, George E. Keylon, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Company. Commercial Airplane Group (page images at HathiTrust) An experimental investigation of the aerodynamic characteristics of nose mounted canard configurations at supersonic Mach numbers (1.5 through 4.5) (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1976., 1976), by James R Burt, Redstone Arsenal (Ala.), Chryler Corporation, and Development United States. Army. Missile Command. Research (page images at HathiTrust) Theoretical analysis of the flow field over a family of ogive bodies : a supplement to MIRADCOM technical report TD-CR-77-5I (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Systems Simulation Directorate, Technology Laboratory, 1979., 1979), by R. L. Richardson, B. Z. Jenkins, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust) Correlation of viscous effects and comparison between experimental and theoretical distribution of potential normal force and pitching moment for bodies of revolution at supersonic speeds (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Labortory, 1967., 1967), by William David Washington, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust) Handbook of supersonic aerodynamics : Section 20, Wind tunnel instrumentation and operation (Washington, D.C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory, 1961., 1961), by R. J. Volluz, Johns Hopkins University. Applied Physics Laboratory, and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust) Investigation of the effect of low thrust levels on the base pressure of a cylindrical body at supersonic speeds (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Labortory, 1970., 1970), by T. A. Martin, C. E. Brazzel, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust) Prediction of unsteady aerodynamic loadings on non-planar wings and wing-tail configurations in supersonic flow. Part I, Theoretical development, program usage, and application (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1972., 1972), by Jack Morito, John R. Hogley, Christopher J. Borland, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Company. Commercial Airplane Group (page images at HathiTrust) Handbook of supersonic aerodynamics. Section 8, Bodies of revolution (Silver Spring, Maryland : The Johns Hopkins University, Applied Physics Laboratory, 1961., 1961), by D. Adamson, I. D. V. Faro, E. A. Bonney, Johns Hopkins University. Applied Physics Laboratory, and United States Bureau of Naval Weapons (page images at HathiTrust) Supersonic symposium : the men of Mach 1 (Air Force Flight Test Center History Office, 1990), by Calif.) Supersonic Symposium (1987 : Edwards Air Force Base and James O. Young (page images at HathiTrust) Spiked blunt bodies in supersonic flow (Mechanics Division, Air Force Office of Scientific Research, Office of Aerospace Research, U. S. Air Force, 1961), by Hyman Harvey Album (page images at HathiTrust)
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