Browse subject: Aerodynamics, Supersonic -- Testing

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Aerodynamics, Supersonic -- Testing

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Filed under: Aerodynamics, Supersonic -- Testing

Static stability and control characteristics of two large-dihedral right triangular pyramid lifting reentry configurations at a mach number of 3.05 / by Charles F. Whitcomb and Willard E. Foss, Jr. (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Charles F. Whitcomb (page images at HathiTrust)
Hypersonic viscous drag on cones in rarefied flow / Marvin I. Kussoy. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by M. I. Kussoy (page images at HathiTrust)
Transonic and supersonic ejection release characteristics of six dynamically scaled external-store shapes from an 0.086-scale model of a current fighter airplane / by William F. Hinson. (Washington D.C. : National Aeronautics and Space Administration, 1959), by William F. Hinson (page images at HathiTrust)
Stability and control characteristics at low subsonic speeds of an airplane configuration having two types of variable-sweep wings / by Bernard Spencer, Jr. (Washington D.C. : National Aeronautics and Space Administration, 1960), by Bernard Spencer (page images at HathiTrust)
An experimental pressure-distribution investigation of interference effects produced at a Mach number of 3.11 by wedge- shaped bodies located under a triangular wing / by Lowell E. Hasel. (Washington D.C. : National Aeronautics and Space Administration, 1959), by Lowell E. Hasel (page images at HathiTrust)
Heat-transfer measurements on a blunt spherical-segment nose to a Mach number of 15.1 and flight performance of the rocket-propelled model to a Mach number of 17.8 / by Charles B. Rumsey and Dorothy B. Lee. (Washington D.C. : National Aeronautics and Space Administration, 1959), by Charles B. Rumsey (page images at HathiTrust)

Filed under: Aerodynamics, Hypersonic -- Testing

Filed under: Hypersonic planes -- Testing

Filed under: Hypersonic planes, Military -- Testing

Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.20 of a V/STOL airplane configuration with a variable-sweep wing and with a skewed wing design / by Odell A. Morris and Gerald V. Foster. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Odell A. Morris (page images at HathiTrust)

Filed under: Hypersonic planes, Military -- Models -- Testing

Static longitudinal stability and control characteristics at a mach number of 2.01 of a hypersonic missile configuration having all-movable wing and tail surfaces / by Ross B. Robinson and Gerald V. Foster. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Ross B. Robinson (page images at HathiTrust)

Filed under: Hypersonic planes -- Materials -- Testing

Filed under: Hypersonic planes -- Models -- Testing

Method for obtaining aerodynamic data on hypersonic configurations with scramjet exhaust flow simulation / William R. Hartill. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by William R. Hartill (page images at HathiTrust)

Filed under: Hypersonic wind tunnels -- Testing

Filed under: Sonic boom -- Testing

Wind-tunnel investigation of the validity of a sonic-boom-minimization concept / Robert J. Mack and Christine M. Darden. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Robert J. Mack (page images at HathiTrust)

Filed under: Supersonic nozzles -- Testing

Aerodynamic and acoustic investigation of inverted velocity profile coannular exhaust nozzle models and development of aerodynamic and acoustic prediction procedures / Richard S. Larson, Douglas P. Nelson, and Bradley S. Stevens ; prepared for Lewis Research Center under contract NAS3-20061. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Richard S. Larson (page images at HathiTrust)

Filed under: Supersonic wind tunnels -- Testing

Wind-tunnel investigation of the validity of a sonic-boom-minimization concept / Robert J. Mack and Christine M. Darden. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Robert J. Mack (page images at HathiTrust)
Boundary-layer velocity profiles downstream of three-dimensional transition trips on a flat plate at Mach 3 and 4 / by John B. Peterson, Jr. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by John B. Peterson (page images at HathiTrust)
Static longitudinal stability and control characteristics at a mach number of 2.01 of a hypersonic missile configuration having all-movable wing and tail surfaces / by Ross B. Robinson and Gerald V. Foster. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Ross B. Robinson (page images at HathiTrust)
Panel flutter studies of boost-vehicle full-scale flight insulation panels / by Michael L. Nacht and Richard L. Greene. (Washington, D.C. : National Aeronautics and Space Administration, 1967), by Michael L. Nacht (page images at HathiTrust)
Some measurements of the dynamic and static stability of two blunt-nosed, low-fineness-ratio bodies of revolution in free flight at M=4 / by Barbara J. Short and Simon C. Sommer. (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Barbara J. Sort (page images at HathiTrust)
Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.20 of a V/STOL airplane configuration with a variable-sweep wing and with a skewed wing design / by Odell A. Morris and Gerald V. Foster. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Odell A. Morris (page images at HathiTrust)
Effectiveness of several control arrangements on a Mercury-type capsule / by Robert I. Sammonds and Robert R. Dickey. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Robert I. Sammonds (page images at HathiTrust)
Wind-tunnel studies at subsonic and transonic speeds of a multiple-mission variable-wing- sweep airplane configuration / by William J. Alford, Jr., Arvo A. Luoma, and William P. Handerson. (Washington, D.C. : National Aeronautics and Space Administration, 1959), by William J. Alford (page images at HathiTrust)

Filed under: Supersonic wind tunnels -- Equipment and supplies -- Testing

Gust generator for a supersonic wind tunnel / Bobby W. Sanders, Allan R. Bishop, and John A. Webb, Jr. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Bobby W. Sanders (page images at HathiTrust)

Items below (if any) are from related and broader terms.

Filed under: Aerodynamics, Supersonic

Vector Polar Method for Shock Interactions With Area Disturbances (technical note DR 4; Berkeley: University of California, 1959), by Antoni K. Oppenheim and Paul A. Urtiew (page images at HathiTrust)
Supersonic aerodynamics and rocket propulsion, by Robert F. Lee. - (Los Angeles, c1963]), by Robert F. Lee (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, Minneapolis-Honeywell Regulator Co., Aeronautical Division, [1956]), by Rudolf Hermann (page images at HathiTrust)
A few remarks on the limitations of linearized theory in supersonic flow. (Cambridge, 1947), by Zdenek Kopal (page images at HathiTrust)
Some considerations of sonic boom. ([Washington, 1961]), by United States. Federal Aviation Agency. Office of Plans (page images at HathiTrust)
Elements of aerodynamics of supersonic flows. (New York, Macmillan Co., 1949), by Antonio Ferri (page images at HathiTrust)
Supersonic aeroelastic effects on static stability and control. Flight Control Laboratory. Contract nos. AF33 (616)-3577 and AF33(616)-6067. ARDC Project no. 8219. Task no. 82158. (Wright-Patterson Air Force Base, Ohio, Wright Air Development Division, Air Research and Development Command., U. S. Air Force, 1958-60), by Bell Aircraft Corporation (page images at HathiTrust)
A study of finite-difference methods as applied to hypersonic viscous shock-layer equations [by] A. L. Chang [and] H. K. Cheng. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1963), by Angela L. Chang (page images at HathiTrust)
Reduction of drag due to lift at supersonic speeds [by] E. W. Graham [and others] (Wright-Patterson Air Force Base, Ohio, Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1954 [i. e. 1955]), by Douglas Aircraft Company (page images at HathiTrust)
Drag due to lift of a not-so-slender configuration; application of theory. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1958), by Robert J. Vidal (page images at HathiTrust)
Linearized theory of conical supersonic flow with application to triangular wings, prepared by W. D. Hayes, S. H. Browne [and] R. J. Law. ([Los Angeles?] North American Aviation, Engineering Dept., 1946, revisions 1947), by North American Aviation (page images at HathiTrust)
Pressure gradient effects on supersonic boundary layer turbulence : final report / A. J. Laderman. (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979), by A. J. Laderman (page images at HathiTrust)
Quasi-three-dimensional supersonic viscid/inviscid interactions including separation effects : final report for period, 1 October 1972- 30 September 1975 / [prepared by Veer N. Vatsa and Michael J. Werle] Aerospace Engineering Dept., University of Cincinnati. (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1975), by Veer N Vetsa (page images at HathiTrust)
Investigation of small surface protuberances upstream of turbulent boundary layer separation produced by a skewed shock wave at Mach 3 / [Robert H. Korkegi], Ramjet Technology Branch, Ramjet Engine Division [Air Force Aero Propulson Laboratory]. (Wright-Patterson Air Force Base, Ohio : Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Syspems Command, 1976), by Robert H Korkegi (page images at HathiTrust)
High speed aerodynamics and jet propulsion. [Board of editors: Theodore von Kármán, chairman, and others] (Princeton, N.J., Princeton University Press, 195?-) (page images at HathiTrust)
Fluctuating loads measured on an over-the-wing supersonic jet model / Conrad M. Willis, Langley Research Center. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Conrad M. Willis (page images at HathiTrust)
The wedge hot-film anemometer in supersonic flow / John M. Seiner. (Washington, D.C. National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by John M. Seiner (page images at HathiTrust)
Control of shock wave - boundary layer interactions by bleed in supersonic mixed compression inlets / Michael K. Fukuda, Warren G. [i.e. R.] Hingst, and Eli Reshotko ; prepared by Case Western Reserve University ... for Lewis Research Center. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Michael K. Fukuda (page images at HathiTrust)
Stability and control characteristics at a mach number of 1.89 of a lightweight glider reentry configuration / by Ross B. Robinson and M. Leroy Spearman. (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Ross B. Robinson (page images at HathiTrust)
Study of lee-side flows over conically cambered delta wings at supersonic speeds / Richard M. Wood and Carolyn B. Watson. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Richard M. Wood (page images at HathiTrust)
Experimental cavity pressure distributions at supersonic speeds / Robert L. Stallings, Jr., and Floyd J. Wilcox, Jr. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Robert L. Stallings (page images at HathiTrust)
Multiscale turbulence effects in supersonic jets exhausting into still air / Khaled S. Abdol-Hamid, Richard G. Wilmoth. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Khaled S. Abdol-Hamid (page images at HathiTrust)
Planform effects on the supersonic aerodynamics of multibody configurations / S. Naomi McMillin and Richard M. Wood. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by S. Naomi McMillin (page images at HathiTrust)
Supersonic aerodynamics of delta wings / Richard M. Wood. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1988), by Richard M. Wood (page images at HathiTrust)
Wing planform effects at supersonic speeds for an advanced fighter configuration / Richard M. Wood and David S. Miller. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by National Technical Information Service], 1984), by Richard M. Wood (page images at HathiTrust)
Theoretical and experimental engine-inlet flow fields for fighter forebodies / Steven F. Yaros. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by Steven F. Yaros (page images at HathiTrust)
Transonic and supersonic Euler computations of vortex-dominated flow fields about a generic fighter / Aga M. Goodsell and John E. Melton. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Aga M. Goodsell (page images at HathiTrust)
Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows / A.R. Porro ... [et al.]. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991) (page images at HathiTrust)
Measurements of forces, moments, and pressures on a generic store separating from a box cavity at supersonic speeds / Robert L. Stallings, Jr., Floyd J. Wilcox, Jr., and Dana K. Forrest. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Robert L. Stallings (page images at HathiTrust)
Longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds / Laurence D. Leavitt. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Laurence D. Leavitt (page images at HathiTrust)
Investigation of flow characteristics over missle bodies at supersonic speeds / Raymond L. Barger and Wallace C. Sawyer. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Raymond L. Barger (page images at HathiTrust)
Experimental aerodynamic characteristics at Mach numbers from 0.60 to 2.70 of two supersonic cruise fighter configurations / Samuel M. Dollyhigh. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Samuel M. Dollyhigh (page images at HathiTrust)
Supersonic wings with significant leading-edge thrust at cruise / A. Warner Robins, Harry W. Carlson and Robert J. Mack. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by A. Warner Robins (page images at HathiTrust)
Lee-side flow over delta wings at supersonic speeds / David S. Miller and Richard M. Wood. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by David S. Miller (page images at HathiTrust)
Supersonic aerodynamic characteristics of canard, tailless, and aft-tail configurations for two wing planforms / Peter F. Covell. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Peter F. Covell (page images at HathiTrust)
Supersonic stability and control characteristics of a cruciform missile model with delta wings and aft tail fin controls / William A. Corlett. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : for sale by the National Technical Information Service], 1979), by William A. Corlett (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 / James C. Townsend ... [et al.]. (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979) (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 / Odell A. Morris, Dennis E. Fuller, and Carolyn B. Watson, Langley Research Center. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Odell A. Morris (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 / by Charles R. McClinton. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Charles R. McClinton (page images at HathiTrust)
Design of a very-low-bleed Mach 2.5 mixed-compression inlet with 45 percent internal contraction / Joseph F. Wasserbauer, Robert J. Shaw, and Harvey E. Neumann. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Joseph F. Wasserbauer (page images at HathiTrust)
Estimation of wing nonlinear aerodynamic characteristics at supersonic speeds / Harry W. Carlson and Robert J. Mack. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Harry W. Carlson (page images at HathiTrust)
Investigation of leading-edge flap performance on delta and double-delta wings at supersonic speeds / Peter F. Covell, Richard M. Wood, and David S. Miller. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Peter F. Covell (page images at HathiTrust)
Progress in supersonic cruise aircraft technology / Cornelius Driver. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Office, 1978), by Cornelius Driver (page images at HathiTrust)
Aerodynamic characteristics of a supersonic fighter aircraft model at Mach 0.40 to 2.47 / Francis J. Capone, E. Ann Bare, Dorothy Arbiter. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Francis J. Capone (page images at HathiTrust)
Supersonic longitudinal aerodynamic characteristics of two space shuttle orbiter configurations / James C. Ellison. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by James C. Ellison (page images at HathiTrust)
Terminal-shock and restart control of a Mach 2.5, axisymmetric, mixed compression inlet with 40 percent internal contraction / by Robert J. Baumbick, Robert E. Wallhagen, and Robert C. Seidel. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Robert J. Baumbick (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 / Joseph F. Wasserbauer, Harvey E. Neumann, and Robert J. Shaw. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Joseph F. Wasserbauer (page images at HathiTrust)
Evaluation of some control-volume techniques for analysis of shock-boundary-layer interactions in supersonic inlets / Warren R. Hingst. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Warren R. Hingst (page images at HathiTrust)
Instantaneous distortion in a Mach 2.5, 40-percent-internal-contraction inlet and its effect on turbojet stall margin / by Paul L. Burstadt and James E. Calogeras. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Paul L. Burstadt (page images at HathiTrust)
Optical measurement of static temperature and hydroxyl radical profiles in a hydrogen-fueled supersonic combustor / by Raymond E. Gaugler. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Raymond E. Gaugler (page images at HathiTrust)
An experimental investigation of nacelle-pylon installation on an unswept wing at subsonic and transonic speeds / John R. Carlson and William B. Compton, III. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by John R. Carlson (page images at HathiTrust)
Body and canard effects on an attached-flow maneuver wing at Mach 1.62 / James L. Pittman and David S. Miller, William H. Mason. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by Jimmy L. Pittman (page images at HathiTrust)
Surface pressure data for a supersonic-cruise airplane configuration at mach numbers of 2.30, 2.96, and 3.30 / Barrett L. Shrout, William A. Corlett, and Ida K. Collins. (Greenbelt, Md. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va : For sale by the National Technical Information Service], 1979), by Barrett L. Shrout (page images at HathiTrust)
Correlations of supersonic boundary-layer transition on cones including effects of large axial variations in wind-tunnel noise / Fang-Jenq Chen, Ivan E. Beckwith and Theodore R. Creel, Jr. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by Fang-Jenq Chen (page images at HathiTrust)
Experimental investigation of leading-edge thrust at supersonic speeds / Richard M. Wood and David S. Miller. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Richard M. Wood (page images at HathiTrust)
Terminal-shock and restart control of a Mach 2.5, mixed-compression inlet coupled to a turbofan engine / by Robert J. Baumbick, Peter G. Batterton, and Carl J. Daniele. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Robert J. Baumbick (page images at HathiTrust)
Control system design using frequency domain models and parameter optimization, with application to supersonic inlet controls / by Robert C. Seidel and Bruce Lehtinen. (Washington, D.C., National Aeronautics and Space Administration, 1974), by Robert C. Seidel (page images at HathiTrust)
Effect of leading-edge load constraints on the design and performance of supersonic wings / Christine M. Carden. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Christine M. Darden (page images at HathiTrust)
The natural flow wing-design concept / Richard M. Wood and Steven X.S. Bauer. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Richard M. Wood (page images at HathiTrust)
Measurements of sonic booms generated by an airplane flying at Mach 3.5 and 4.8 / by Karen S. Green and Terrill W. Putnam. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Karen S. Green (page images at HathiTrust)
Continuous-output terminal-shock-position sensor for mixed-compression inlets evaluated in wind-tunnel tests of YF-12 aircraft inlet / by Miles O. Dustin, Gary L. Cole, and George H. Neiner. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Miles O. Dustin (page images at HathiTrust)
Concept development of a Mach 3.0 high-speed civil transport / A. Warner Robins ... [et al.]. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988) (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 / William G. Costakis. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by William G. Costakis (page images at HathiTrust)
Longitudinal and lateral-directional aerodynamic characteristics of a wing-cone configuration at Mach numbers from 2.5 to 4.5 / Peter F. Covell, Ira J. Walker, Dorothy T. Howell. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Peter F. Covell (page images at HathiTrust)
Reevaluation of compressible-flow Preston tube calibrations / Jerry M. Allen. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Jerry M. Allen (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 / A.B. Blair, Jr. ; Langley Research Center, Hampton, Va. (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by A. B. Blair (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 / A.B. Blair, Jr. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by A. B. Blair (page images at HathiTrust)
Computer program for supersonic kernel-function flutter analysis of thin lifting surfaces / by Herbert J. Cunningham. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Herbert J. Cunningham (page images at HathiTrust)
Supersonic aerodynamic characteristics of a series of wrap-around-fin missile configurations / Roger H. Fournier. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Roger H. Fournier (page images at HathiTrust)
Theoretical evaluation of high-speed aerodynamics for arrow-wing configurations / Samuel M. Dollyhigh, Langley Research Center. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Samuel M. Dollyhigh (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 / Barrett L. Shrout. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Barrett L. Shrout (page images at HathiTrust)
Wind-tunnel investigation at supersonic speeds of a canard-controlled missile with fixed and free-rolling tail fins / A.B. Blair, Jr., Langley Research Center. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by A. B. Blair (page images at HathiTrust)
Supersonic aerodynamic characteristics of a Sparrow III type missile model with wing controls and comparison with existing tail-control results / William J. Monta. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by William J. Monta (page images at HathiTrust)
Mechanical characteristics of stability-bleed valves for a supersonic inlet / George H. Neiner, Miles O. Dustin, and Gary L. Cole. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by George H. Neiner (page images at HathiTrust)
Application of a two-dimensional unsteady viscous analysis code to a supersonic throughflow fan stage / Ronald J. Steinke. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by Ronald J. Steinke (page images at HathiTrust)
Supersonic aerodynamic characteristics of a proposed assured crew return capability (ACRC) lifting-body configuration / George M. Ware. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by George M. Ware (page images at HathiTrust)
Low-speed static and dynamic force tests of a generic supersonic cruise fighter configuration / David E. Hahne. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by David E. Hahne (page images at HathiTrust)
Cold-flow acoustic evaluation of a small-scale, divergent, lobed nozzle for supersonic jet noise suppression / Ronald G. Huff and Donald E. Groesbeck. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Ronald G. Huff (page images at HathiTrust)
Performance of vortex generators in a Mach 2.5 low-bleed full-scale 45-percent-internal-contraction axisymmetric inlet / Harvey E. Neumann, Joseph F. Wasserbauer, and Robert J. Shaw. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Harvey E. Neumann (page images at HathiTrust)
A study of the sonic-boom characteristics of a blunt body at a Mach number of 4.14 / Harry W. Carlson and Robert J. Mack ; NASA Langley Research Center. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield Va. : For sale by the National Technical Information Service, 1977), by Harry W. Carlson (page images at HathiTrust)
Experimental investigation to validate use of cryogenic temperatures to achieve high Reynolds numbers in boattail pressure testing / David E. Reubush ; Langley Research Center, Hampton, Va. (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by David E. Reubush (page images at HathiTrust)
Effects of Reynolds number and model support on the supersonic aerodynamic chacteristics of a 140° included-angle cone / by Charles D. Trescot, Jr., and Clarence A. Brown, Jr., and Dorothy T. Howell. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Charles D. Trescot (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 / Robert L. Stallings, Jr. and Milton Lamb. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Robert L. Stallings (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 / by Glenn A. Mitchell and Bobby W. Sanders. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Glenn A. Mitchell (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 / by Robert J. Shaw, Glenn A. Mitchell, and Bobby W. Sanders. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Robert J. Shaw (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 / by Robert J. Shaw, Glenn A. Mitchell, and Bobby W. Sanders. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Robert J. Shaw (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 / by Robert J. Shaw, Glenn A. Mitchell, and Bobby W. Sanders. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Robert J. Shaw (page images at HathiTrust)
Modification of a three-dimensional supersonic nozzle analysis and comparison with experimental data / by Allan R. Bishop and Bobby W. Sanders. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Allan R. Bishop (page images at HathiTrust)
Comparison of theoretical and experimental boundary-layer development in a Mach 2.5 mixed-compression inlet / by Warren R. Hingst and Charles E. Towne. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Warren R. Hingst (page images at HathiTrust)
A method for calculating a real-gas two-dimensional nozzle contour including the effects of gamma / Charles B. Johnson and Lillian R. Boney. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles B. Johnson (page images at HathiTrust)
Aerodynamic characteristics of a hypersonic research airplane concept having a 70 ̊swept double-delta wing at Mach number 0.2 / Jim A. Penland, Theodore R. Creel, Jr., and James L. Dillion, Langley Research Center. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Jim A. Penland (page images at HathiTrust)
Theoretical and experimental flow fields for a supersonic cruise fighter forebody / Steven F. Yaros. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Steven F. Yaros (page images at HathiTrust)
Numerical simulation of steady supersonic viscous flow / Lewis B. Schiff and Joseph L. Steger. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Lewis B. Schiff (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 / Harry W. Carlson, Langley Research Center. (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Harry W. Carlson (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 / David S. Miller ... [et al.]. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981) (page images at HathiTrust)
Evaluation by step response tests of prototype relief valves designed for YF-12 inlet stability bleed system / Miles O. Dustin and George H. Neiner. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Miles O. Dustin (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 / Laurence D. Leavitt and Long P. Yip. ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Laurence D. Leavitt (page images at HathiTrust)
Effect of afterburner lights and inlet unstarts on a mixed-compression-inlet turbofan engine operating at Mach 2.5 / Robert J. Baumbick, Peter G. Batterton, and Carl J. Daniele. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Robert J. Baumbick (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 / Robert L. Stallings Jr. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Robert L. Stallings (page images at HathiTrust)
An experimental and analytical study of the aerodynamic interference effects between two Sears-Haack bodies at Mach 2.7 / Jeffrey W. Bantle. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Jeffrey W. Bantle (page images at HathiTrust)
Supersonic dynamic-stability derivatives of the space shuttle launch vehicle / Richard P. Boyden, Delma C. Freeman, Jr., and Edwin E. Davenport. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1976), by Richmond P. Boyden (page images at HathiTrust)
Some observations on a new numerical method for solving the Navier-Stokes equations / Ajay Kumar. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Ajay Kumar (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 / Milton Lamb, Wallace C. Sawyer, and James L. Thomas. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Milton Lamb (page images at HathiTrust)
Theoretical and experimental investigation of supersonic aerodynamic characteristics of a twin-fuselage concept / Richard M. Wood, David S. Miller, and Kenneth S. Brentner. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Richard M. Wood (page images at HathiTrust)
A study of the sonic-boom characteristics of a blunt body at a Mach number of 6 / George C. Ashby, Jr. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by George C. Ashby (page images at HathiTrust)
Mechanical property characterization of Borsic®/aluminum laminates at room and elevated temperatures / Robert R. McWithey and Dick M. Royster. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Robert R. McWithey (page images at HathiTrust)
Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft / Bobby L. Berrier and Richard J. Re. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Bobby L. Berrier (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 / Jimmy L. Pittman and Gregory D. Riebe. ([Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Jimmy L. Pittman (page images at HathiTrust)
Steady and nonsteady supersonic turbulent afterbody flow / Kenneth K. Yoshikawa and Alan A. Wray. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Kenneth K. Yoshikawa (page images at HathiTrust)
Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds / Robert L. Stallings, and Milton Lamb. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Robert L. Stallings (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 / Gregory D. Riebe, William J. Small, and Odell A. Morris. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Gregory D. Riebe (page images at HathiTrust)
Experimental investigation of porous-floor effects on cavity flow fields at supersonic speeds / Floyd J. Wilcox, Jr. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Floyd J. Wilcox (page images at HathiTrust)
Effect on tail-fin span on stability and control characteristics of a canard-controlled missile at supersonic Mach numbers / A.B. Blair, Jr., Jerry M. Allen, and Gloria Hernandez. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by A. B. Blair (page images at HathiTrust)
Low-speed aerodynamic characteristics of a highly swept, untwisted, uncambered arrow wing / Paul L. Coe, Jr., Scott O. Kjelgaard, and Garl L. Gentry, Jr. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For the sale by the National Technical Information Service], 1983), by Paul L. Coe (page images at HathiTrust)
Experimental evaluation of a Mach 3.5 axisymmetric inlet / J. Syberg and J.L. Koncsek. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1975]), by J. Syberg (page images at HathiTrust)
Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations : volume II - code description / Frank Marconi, and Larry Yaeger ; prepared by Grumman Aerospace Corporation, Bethpage, N.Y. for Langley Research Center, Hampton, Va. (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Frank Marconi (page images at HathiTrust)
Effect of interjet spacing on mixing of multiple coaxial jets in supersonic flow / by A.K. Lorber and J.A. Schetz. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by A. K. Lorber (page images at HathiTrust)
A computational system for aerodynamic design and analysis of supersonic aircraft : part 3-computer program description / W.D. Middleton, J.L. Lundry and R.G. Coleman ; prepared by Boeing Commercial Airplane Company, Seattle, Wash. for Langley Research Center. (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by W. D. Middleton (page images at HathiTrust)
A computational system for aerodynamic design and analysis of supersonic aircraft : part 1-general description and theoretical development / W.D. Middleton, and J.L. Lundry ; prepared by Boeing Commercial Airplane Company, Seattle, Wash. for Langley Research Center. (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by W. D. Middleton (page images at HathiTrust)
A System for aerodynamic design and analysis of supersonic aircraft. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980) (page images at HathiTrust)
Development of the triplet singularity for the analysis of wings and bodies in supersonic flow / F.A. Woodward ; prepared for Langley Research Center under contract NAS1-15792. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by F. A. Woodward (page images at HathiTrust)
Calculation of three-dimensional, inviscid supersonic, steady flows / Gino Moretti ; prepared for Langley Research Center under grant NSG-1248. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by Gino Moretti (page images at HathiTrust)
Viscous computations of cold air/air flow around scramjet nozzle afterbody / Oktay Baysal and Walter C. Engelund. (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Oktay Baysal (page images at HathiTrust)
Study of supersonic wings employing the attainable leading-edge thrust concept / W.D. Middleton ; prepared for Langley Research Center under grant NAS1-15534. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by W. D. Middleton (page images at HathiTrust)
Bumblebee Program - aerodynamic data / G.A. Barnes and L.L. Cronovich ; prepared for Langley Research Center under contract L-60036A. (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by G. A. Barnes (page images at HathiTrust)
Effects of mach number and wall-temperature ratio on turbulent heat transfer at mach numbers from 3 to 5, by Thorval Tendeland. ([Washington, U.S. G.P.O.], 1959), by Thorval Tendeland (page images at HathiTrust)
Jet effects at supersonic speeds on base and afterbody pressures of a missile model having single and multiple jets / by Nickolai Charczenko and Clyde Hayes. (Washington, D.C. : National Aeronautics and Space Administration, [1963]), by Nickolai Charczenko (page images at HathiTrust)
Static stability and separation characteristics of a two-stage rocket configuration at Mach numbers from 1.57 to 4.50 / by Kenneth L. Turner, David S. Shaw, and Laurence W. Enderson, Jr. (Washington : National Aeronautics and Space Administration, [1960]), by Kenneth L. Turner (page images at HathiTrust)
Supersonic longitudinal stability characteristics of the two final stages of a four-stage launch vehicle / by Royce L. McKinney. (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1964]), by Royce L. McKinney (page images at HathiTrust)
An experimental investigation of the flow in an axisymmetric internal-compression inlet for M=2.75 / by Earl C. Watson and William P. Peterson. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1961]), by Earl C. Watson (page images at HathiTrust)
Turbulence measurements in supersonic, shock-free jets by the optical crossed-beam method / by M.J. Fisher and K.D Johnston. (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., 1970), by M. J. Fisher (page images at HathiTrust)
Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 / by Robert W. Cubbison, Bernhard H. Anderson, and James J. Ward. (Washington : National Aeronautics and Space Administration, [1961]), by Robert W. Cubbison (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 / by Warren Gillespie, Jr. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Warren Gillespie Jr. (page images at HathiTrust)
Flutter of buckled, simply supported, rectangular panels at supersonic speeds / by Robert W. Fralich and John A. McElman. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Robert W. Fralich (page images at HathiTrust)
Static aerodynamic characteristics, pressure distributions, and RAM-air inflation of attached inflatable decelerator models at Mach 3.0 / William D. Deveikis and James Wayne Sawyer. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by William D. Deveikis (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 / by Lado Muhlstein, Jr., and Richard G. Beranek. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1971]), by Lado Muhlstein (page images at HathiTrust)
Systematic study of error sources in supersonic skin-friction balance measurements / Jerry M. Allen ; Langley Research Center. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Jerry M. Allen (page images at HathiTrust)
Effect of nonlifting empennage surfaces on single-engine afterbody/nozzle drag at Mach numbers from 0.5 to 2.2 / Bobby L. Berrier. (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Bobby L. Berrier (page images at HathiTrust)
Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction / Joseph F. Wasserbauer. (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Joseph F. Wasserbauer (page images at HathiTrust)
Experimental preston tube and law-of-the-wall study of turbulent skin friction on axisymmetric bodies at supersonic speeds / Jerry M. Allen. (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Jerry M. Allen (page images at HathiTrust)
An improved method for calculating supersonic pressure fields about bodies of revolution / by Robert J. Mack. (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Robert J. Mack (page images at HathiTrust)
A study of helium penetration and spreading in a Mach 2 airstream using a delta wing injector / Louis A. Povinelli, Frederick P. Povinelli, and Martin Hersch. (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1969), by Louis A. Povinelli (page images at HathiTrust)
A study of the application of heat or force fields to the sonic-boom-minimization problem / David S. Miller and Harry W. Carlson. (Washington, D.C. : National Aeronautics and Space Administration, 1969), by David S. Miller (page images at HathiTrust)
A structural merit function for aerodynamic decelerators / Melvin S. Anderson, Herman L. Bohon, Martin M. Mikulas, Jr. (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Melvin S. Anderson (page images at HathiTrust)
Supersonic aerodynamics of large-angle cones / James F. Campbell, Dorothy T. Howell. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by James F. Campbell (page images at HathiTrust)
A mathematical analysis of supersonic inlet dynamics / Ross G. Willoh. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1968), by Ross G. Willoh (page images at HathiTrust)
Application of a one-strip integral method to the unsteady supersonic aerodynamics of an inclined flat surface / Robert M. Bennett. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by Robert M. Bennett (page images at HathiTrust)
Design and performance of a digital electronic normal shock position sensor for mixed-compression inlets / by Gary L. Cole, George H. Neiner, and Michael J. Crosby. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by Gary L. Cole (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 / by Raul J. Conti. (Washington : National Aeronautics and Space Administration, [1959]), by Raul J. Conti (page images at HathiTrust)
Experimental heat-transfer distributions on a blunt lifting body at Mach 3.71 / by Robert A. Stallings, Jr., Robert L. Wright, and Ida K. Collins. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1970]), by Robert L. Stallings (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 ̊/ by Lovick O. Hayman, Jr., amd Russell W. McDearmon. (Washington : National Aeronautics and Space Administration, [1962]), by Lovick O. Hayman (page images at HathiTrust)
Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 / by Charles B. Rumsey, Robert O. Piland, and Russell N. Hopko. (Washington : National Aeronautics and Space Administration, [1960]), by Charles B. Rumsey (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 / by Carlton S. James. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Carlton S. James (page images at HathiTrust)
Experimental nozzle expansion and flow characteristics of potassium vapor / by Louis J. Goldman and Stanley M. Nosek. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1966]), by Louis J. Goldman (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 / by Harry W. Carlson. (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Harry W. Carlson (page images at HathiTrust)
The lateral and directional aerodynamic characteristics of a re-entry configuration based on a blunt 13° half cone at Mach numbers to 0.90 / by George C. Kenyon. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by George C. Kenyon (page images at HathiTrust)
Transonic and supersonic flutter trend investigation of a variable-sweep wing / by John C. Stonesifer and Robert C. Goetz. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by John C. Stonesifer (page images at HathiTrust)
Low-speed investigation of the aerodynamic characteristics of a variable-sweep supersonic transport configuration having a blended wing and body / by William C. Sleeman, Jr., and A. Warner Robins. (Washington, D.C. : National Aeronautics and Space Administration, [1961]), by William C. Sleeman (page images at HathiTrust)
A method for calculating the aerodynamic loading on wing-body combinations at small angles of attack in supersonic flow / by Charles M. Jackson, Jr. and Wallace C. Sawyer. (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Charlie M. Jackson (page images at HathiTrust)
Thermoelastic damping and its effect on flutter of stressed panels situated in a supersonic airflow / by R.C. Shieh. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by R. C. Shieh (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 / by Louis S. Stivers, Jr. (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Louis S. Stiver (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 / by Vernon Van Hise. (Washington : National Aeronautics and Space Administration, [1959]), by Vernon Van Hise (page images at HathiTrust)
Spectrographic temperature measurements in a carbon-arc-powered air jet / by David H. Greenshields. (Washington : National Aeronautics and Space Administration, [1959]), by David H. Greenshields (page images at HathiTrust)
Aerodynamic loading characteristics of a 1/10-scale model of the three-stage Scout vehicle at Mach numbers 1.57 to 4.65 / by Lloyd S. Jernell. (Washington : National Aeronautics and Space Administration, [1963]), by Lloyd S. Jernell (page images at HathiTrust)
Effects of Reynolds number and flow incidence on the force characteristics of a family of flat-front cylinders / Vernard E. Lockwood. (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Vernard E. Lockwood (page images at HathiTrust)
Concentration measurements of an injected gas in a supersonic stream / by Marvin G. Torrence. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1967]), by Marvin G. Torrence (page images at HathiTrust)
Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions / by Helmut F. Butze, Arthur M. Trout, and Harry M. Moyer. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1969), by Helmut F. Butze (page images at HathiTrust)
Static thrust of an annular nozzle with a concave central base / by Blake W. Corson Jr. and Charles E. Mercer. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Blake W. Corson (page images at HathiTrust)
A method for calculating aerodynamic loadings on thin wings at a Mach number of 1 / by John L. Crigler. (Washington : National Aeronautics and Space Administration), by John L. Crigler (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 / by Robert J. Keynton and Ann B. Fichter. (Washington : National Aeronautics and Space Administration, [1961]), by Robert J. Keynton (page images at HathiTrust)
Accuracy of pitot-pressure rakes for turbulent boundary-layer measurements in supersonic flow / by Earl R. Keener and Edward J. Hopkins. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1971), by Earl R. Keener (page images at HathiTrust)
Flutter of flat rectangular orthotropic panels with biaxial loading and arbitrary flow direction / by Herman L. Bohon. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1963]), by Herman L. Bohon (page images at HathiTrust)
Supersonic investigation of nozzle hinge moments of a modified Saturn C-1 model with and without jet flow / by Nickolai Charczenko and Jerry L. Lowery. (Washington, D.C. : National Aeronautics and Space Administration, [1963]), by Nickolai Charczenko (page images at HathiTrust)
Loads induced on a flat plate at a Mach number of 4.5 with a sonic or supersonic jet exhausting normal to the surface / by William Letko. (Washington : National Aeronautics and Space Administration, [1963]), by William Letko (page images at HathiTrust)
Static aerodynamic characteristics of three rocket-vehicle configurations at Mach numbers from 1.80 to 4.63 including some effects of fin size, fin cant, and auxiliary rocket motors / by Dennis E. Fuller and Gerald V. Foster. (Washington : National Aeronautics and Space Administration, [1963]), by Dennis E. Fuller (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 / by Lloyd S. Jernell. (Washington : National Aeronautics and Space Administration, [1963]), by Lloyd S. Jernell (page images at HathiTrust)
Pressure measurements of the leading edge of a swept wing at Mach 2.2 / by Russell B. Sorrells III. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Russell B. Sorrells (page images at HathiTrust)
Performance of three isentropic all internal compression axisymmetric inlets designed for Mach 2.5 / by Bernhard H. Anderson and David N. Bowditch. (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Bernhard H. Anderson (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° / by Gerald V. Foster. (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Gerald V. Foster (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 / by Simon C. Sommer. (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Simon C. Sommer (page images at HathiTrust)
Experimental and calculated supersonic flutter characteristics of models of the x-15 horizontal and vertical tails / by William T. Lauten, Jr., and Robert W. Hess. (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by William T. Lauten (page images at HathiTrust)
Correlation of secondary sonic and supersonic gaseous jet penetration into supersonic crossflows / by Frederick P. Povinelli and Louis A. Povinelli. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1971]), by Frederick P. Povinelli (page images at HathiTrust)
The effects of wing-tip droop on the aerodynamic characteristics of a delta-wing aircraft at supersonic speeds / by Richard H. Peterson. (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Richard H. Peterson (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 / by William F. Hinson. (Washington, D.C. : National Aeronautics and Space Administration, 1961), by William F. Hinson (page images at HathiTrust)
Handbook of supersonic aerodynamics. (Washington, Bureau of Ordnance, 1950-), by Silver Spring Johns Hopkins University. Applied Physics Laboratory (page images at HathiTrust)
Flight test and analysis of the rolling motions of a 79 ̊clipped delta configuration with wing-tip fins at supersonic speeds / James L. Raper. (Washington, D.C. : National Aeronautics and Space Administration, 1963), by James L. Raper (page images at HathiTrust)
Performance of several conical convergent-divergent rocket-type exhaust nozzles / by C.E. Campbell and J.M. Farley. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by C. E. Campbell (page images at HathiTrust)
Pressure distribution on a body a revolution in supersonic flight, by Robert R. Reynolds. ([Washington, U. S. Dept. of Commerce, National Bureau of Standards], 1952), by Robert Ramon Reynolds (page images at HathiTrust)
Reverse flow and supersonic interference. ([Providence, Division of Engineering, Brown University], 1958), by Joseph H. Clarke (page images at HathiTrust)
Engineering supersonic aerodynamics. (New York, McGraw-Hill, 1950), by E Arthur Bonney (page images at HathiTrust)
An analysis of nuclear-rocket nozzle cooling / by Willian H. Robbins, Daniel Bachkin and Arthur A. Medeiros. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by William H. Robbins (page images at HathiTrust)
Some divergence characteristics of low-aspect-ratio wings at transonic and supersonic speeds / by Donald L. Woolston, Frederick W. Gibson and Herbert J. Cunningham. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Donald S. Woolston (page images at HathiTrust)
Investigation of the flow over simple bodies at Mach numbers of the order of 20 / by Arthur Henderson, Jr. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Arthur Henderson (page images at HathiTrust)
Aerodynamics of supersonic flight; an introduction. (New York, Pitman Pub. Corp., [1950]), by Alan Pope (page images at HathiTrust)
Nonsteady discharge of subcritical flow / by George Rudinger. (Princeton, N.J. : Project Squid Headquarters, James Forrestal Research Center, Princeton University, 1960), by George Rudinger (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 / by Alvin H. Sacks, Jack A. Burnell. (Palo Alto, Calif. : Vidya, a division of Itek Corp., 1963), by Alvin Howard Sacks (page images at HathiTrust)
Material presented at the NACA Conference on Supersonic Aerodynamics at Ames Aeronautical Laboratory on June 4, 1946, National Advisory Committee for Aeronautics. ([Washington?, 1946?]), by United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
Supersonic aerodynamics and rocket propulsion, by Robert F. Lee. (Los Angeles, c1963]), by Robert F. Lee (page images at HathiTrust)
Studies on the validity of the hydraulic analogy to supersonic flow [initiated by A. T. Ippen; work carried out and report prepared by D. R. F. Harleman and others] (Wright-Patterson Air Force Base, Dayton, Ohio, U. S. Air Force, Air Material Command, 1950-52 [pt. 1, rev. 1951]), by Massachusetts Institute of Technology. Department of Civil Engineering (page images at HathiTrust)
Tables of supersonic flow around cones of large yaw, by the staff of the Computing Section, Center of Analysis, under the direction of Zdeněk Kopal. (Cambridge, 1949), by Massachusetts Institute of Technology Center of Analysis Computing Section (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 / by F.W. Geiger [and] C.W. Mautz; with an addendum by R.N. Hollyer, jr.; Supervised by Otto Laporte. (Washington, [1949]), by Frederick William Geiger (page images at HathiTrust)

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