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Hypersonic planes, Military -- Testing

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• Hypersonic planes, Military
• Airplanes, Military -- Testing
• Hypersonic planes -- Testing
• Testing

• Hypersonic planes, Military -- Models -- 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 (National Aeronautics and Space Administration, 1961), by Odell A. Morris, Gerald V. Foster, and Langley Research Center (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 (National Aeronautics and Space Administration, 1961), by Ross B. Robinson, Gerald V. Foster, and Langley Research Center (page images at HathiTrust)

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

• Future Air Force requirements for hydrocarbon fuels (Wright-Patterson Air Force Base, Ohio : Directorate of Materials and Processes, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by Jack R. Fultz and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Pressure measurement at Mach 19 for a winged re-entry configuration : part of an investigation of hypersonic flow separation and control characteristics (Wright-Patterson Air Force Base, Ohio : Flight Control Division, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by Stavros A. Hartofilis, United States. Air Force. Systems Command. Aeronautical Systems Division, and Grumman Aircraft Engineering Corporation (page images at HathiTrust)
• Flow regimes for hypervelocity vehicles (Wright-Patterson Air Force Base, Ohio : Directorate of Aeromechanics, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by Anthony Casaccio, Edgar Bendor, Republic Aviation Corporation, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Fluctuating pressure loads for hypersonic vehicle structures : phase I (Wright-Patterson Air Force Base, Ohio : Fliight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, 1991, 1991), by Henry G. Lew, Anthony L. Laganelli, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and Science Applications International Corporation (page images at HathiTrust)
• Zeus user manual "real gas" effects (Dahlgren, Virginia : Naval Surface Weapons Center, Research and Technology Department, 1991., 1991), by F. J. Priolo, A. B. Wardlaw, and Naval Surface Warfare Center (U.S.). Dahlgren Division (page images at HathiTrust)

• Static stability and drag characteristics of a hypersonic aircraft design at Mach numbers 1.5 to 5.6 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1975., 1975), by J. T. Jr Best, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)

• Hypersonic Technology for Military Application (1989), by National Research Council Commission on Engineering and Technical Systems (page images with commentary at NAP)

• Fidelity analysis for the OH-58D Kiowa Warrior crew trainer (U.S. Army Research Institute for the Behavioral and Social Sciences, 1998), by John E. Stewart, Robert H. Wright, Kenneth D. Cross, and U.S. Army Research Institute for the Behavioral and Social Sciences (page images at HathiTrust)
• Parametric fatigue analysis of USAF aircraft (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Directorate of Laboratories, Air Force Systems Command, United States Air Force, 1967., 1967), by George J. Roth, James C. Sliemers, John P. Ryan, Air Force Flight Dynamics Laboratory (U.S.), and University of Dayton. Research Institute (page images at HathiTrust)

• Limited evaluation of an F-14A airplane utilizing an aileron-rudder inter-connect control system in the landing configuration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Wendell W. Kelley, Einar K. Enevoldson, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Hugh L. Dryden Flight Research Center, and Langley Research Center (page images at HathiTrust)
• Expanded operational capabilities of the Langley Mach 7 scramjet test facility (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Scott R. Thomas, Robert W. Guy, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• An analysis of flight test data on the C-141A aircraft (National Aeronautics and Space Administration ;, 1970), by J. H. Paterson, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• XB-70 flight test data comparisons with simulation predictions of inlet unstart and buzz (National Aeronautics and Space Administration ;, 1970), by Arnold W. Martin, Warren D. Beaulieu, Flight Research Center (U.S.), and North American Rockwell Corporation (page images at HathiTrust)
• NASA TN D-6655 (National Aeronautics and Space Administration :, 1972), by William H. Andrews, Richard R. Larson, Glenn H. Robinson, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Crash of the F-14A. : Report, Ninety-second Congress, first session, under authority of H. Res. 201. (U.S. Govt. Print. Off, 1971), by United States. Congress. House. Committee on Armed Services. Armed Services Investigating Subcommittee (page images at HathiTrust)
• C-130BL category I performance test and qualitative stability and control evaluation (U.S. Air Force, Air Research and Development Command, Air Force Flight Test Center, 1961), by Kenneth C. Carter, Emil Sturmthal, and Air Force Flight Test Center (U.S.) (page images at HathiTrust)

• A career in test and evaluation : reflections and observations : from an oral history interview of Charles E. "Pete" Adolph (Air Force History and Museums Program in association with Air University Press, 1998), by Charles E. Adolph, Richard Hallion, and Air University (U.S.). Press (page images at HathiTrust)

• Stability and control characteristics of a three-surface advanced fighter configuration at angles of attack up to 45? (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by William P. Henderson, Laurence D. Leavitt, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Pressures measured in flight on the aft fuselage and external nozzle of a twin-jet fighter (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Jack Nugent and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effect on empennage location on twin-engine afterbody/nozzle aerodynamic characteristics at Mach numbers from 0.6 to 1.2 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Laurence D. Leavitt and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effects of twin-vertical-tail parameters on twin-engine afterbody/nozzle aerodynamic characteristics (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Laurence D. Leavitt, E. Ann Bare, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Flight tests of a twin-duct induction system for a mach number range of 0.78 to 2.07 (National Aeronautics and Space Administration, 1960), by Jack Nugent, Bruce G. Powers, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flight investigation of a small side-located control stick used with electronic control systems in a fighter airplane (National Advisory Committee for Aeronautics, 1957), by S. A. Sjoberg, William L. Alford, Walter R. Russell, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• In-flight investigation of the effects of higher-order control system dynamics on longitudinal handling qualities (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1968., 1968), by Dante A. Di Franco, Cornell Aeronautical Laboratory, Air Force Flight Dynamics Laboratory (U.S.), and Air Force Wright Aeronautical Laboratories (page images at HathiTrust)

• Fifty-seven years of development and validation of aeronautical technology, 1940-1997 (National Aeronautics and Space Administration, Ames Research Center ;, 1999), by Paul F Borchers, Jay W Fletcher, James A Franklin, and Ames Research Center (page images at HathiTrust)

• Against the wind : 90 years of flight test in the Miami Valley. (History Office, Aeronautical Systems Center, Air Force Materiel Command ;, 1994), by United States. Air Force. Systems Command. Aeronautical Systems Division. History Office (page images at HathiTrust)

• Testing and operational requirements for the B-2 Bomber : hearing before the Committee on Armed Services, United States Senate, One Hundred First Congress, first session, July 21, 1989. (U.S. G.P.O. :, 1989), by United States Senate Committee on Armed Services (page images at HathiTrust)

• Subsonic aerodynamic characteristics of an airplane configuration utilizing a variable-sweep wing having a free-floating apex (National Aeronautics and Space Administration :, 1965), by Edward C. Polhamus, Alexander D. Hammond, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)

• Low-speed investigation of effects of vertical tails on the static stability characteristics of a canard-bomber configuration having a very thin wing and a slender elliptical fuselage (National Aeronautics and Space Administration, 1961), by Thomas G. Gainer and Langley Research Center (page images at HathiTrust)

• Investigation of Axisymmetric and nonaxisymmetric nozzels installed on a 0.10-scale F-18 protype airplane model (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Francis J. Capone, Bobby L. Berrier, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Comparison of wind tunnel and flight test afterbody and nozzle pressures for a twin-jet fighter aircraft at transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1987), by Jack Nugent, Odis C. Pendergraft, and Ames Research Center (page images at HathiTrust)
• Effects of external stores on the aerodynamic characteristics of a 60 ̊Delta-wing fighter model at mach 1.60 to 2.87 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by M. Leroy Spearman, William J. Monta, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Low-speed wind-tunnel investigation of the effect of strakes and nose chines on lateral-directional stability of a fighter configuration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Jay M. Brandon and Langley Research Center (page images at HathiTrust)
• NASA TN D-6117 (National Aeronautics and Space Administration ;, 1971), by Frederick L. Moore, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Transonic and supersonic ejection release characteristics of six dynamically scaled external-store shapes from an 0.086-scale model of a current fighter airplane (National Aeronautics and Space Administration, 1959), by William F. Hinson and Langley Research Center (page images at HathiTrust)
• An experimental pressure-distribution investigation of interference effects produced at a Mach number of 3.11 by wedge- shaped bodies located under a triangular wing (National Aeronautics and Space Administration, 1959), by Lowell E. Hasel and Langley Research Center (page images at HathiTrust)
• Heat-transfer measurements on a blunt spherical-segment nose to a Mach number of 15.1 and flight performance of the rocket-propelled model to a Mach number of 17.8 (National Aeronautics and Space Administration, 1959), by Charles B. Rumsey, Dorothy B. Lee, and Langley Research Center (page images at HathiTrust)

• Buffet characteristics of the model F-4 airplane in the transonic flight regime (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1970., 1970), by Marshall Cohen, Air Force Flight Dynamics Laboratory (U.S.), McDonnell Aircraft Company, and United States. Air Force. Systems Command (page images at HathiTrust)
• Final test report : X-29A Vortex Flow Control (VFC) flight test results (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate , Wright Laboratory, Air Force Materiel Command, United States Air Force, 1993., 1993), by Frank Luria, Brian Hobbs, Paul Pellicano, Joseph Krumenacker, William Gillard, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and Grumman Aircraft Engineering Corporation (page images at HathiTrust)

• Transonic aerodynamic characteristics of a variable-sweep airplane configuration having a 12-percent-thick wing and an inboard pivot location (National Aeronautics and Space Administration, 1960), by Ralph P. Bielat, P. Kenneth Pierpont, and Langley Research Center (page images at HathiTrust)

• Transonic wind-tunnel investigation of the effect of control span and large wing-tip nacelles on effectiveness of spoiler-slot-deflector controls on an unswept-wing fighter-type airplane (National Aeronautics and Space Administration, 1960), by Dewey E. Wornom and Langley Research Center (page images at HathiTrust)

• Effects of wing incidence on the longitudinal trim characteristics of a cambered 70 degree delta-wing configuration at mach numbers 3.0 to 5.0 (National Aeronautics and Space Administration, 1960), by Warren F. Ahtye and Ames Research Center (page images at HathiTrust)
• Static longitudinal stability characteristics of various Mercury escape configurations and of a proposed alternate escape configuration for Mach numbers of 0.05 to 9.60 (National Aeronautics and Space Administration, 1961), by Robert P. Smith, William C. Moseley, and United States. National Aeronautics and Space Administration. Space Task Group (page images at HathiTrust)
• A compilation of wind-tunnel heat-transfer measurements on the afterbody of the Project Mercury capsule reentry configuration (National Aeronautics and Space Administration, 1961), by Kenneth C. Weston, Joanna E. Swanson, and United States. National Aeronautics and Space Administration. Space Task Group (page images at HathiTrust)

• Residual strength and crack propagation tests on C-130 airplane center wings with service-imposed fatigue damage (National Aeronautics and Space Administration ;, 1972), by H. Lawrence Snider, William Dirkin, Franklin L. Reeder, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)

• Wind-tunnel evaluation of a 21-percent-scale powered model of a prototype advanced scout helicopter (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Arthur E. Phelps, John D. Berry, and United States. Army Aviation Systems Command. Structures Laboratory (page images at HathiTrust)

• Modified Influence Function Method (MIF) for weapn separation prediction : verison 1.0 (Wright Patterson Air Force Base, Ohio : Flight Dynamics Directorate , Wright Laboratory, Air Force Materiel Command, United States Air Force, 1994., 1994), by Mark A. Pinney and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)

• Experimental quiet engine program : summary report (National Aeronautics and Space Administration ;, 1975), by W. G. Cornell, United States National Aeronautics and Space Administration, Lewis Research Center, and General Electric Company (page images at HathiTrust)

• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1945), by Roy H. Lange, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

More items available under broader and related terms at left.