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Jet fighter planes

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Fighter jet planes

Filed under: Jet fighter planes

Wind-tunnel investigation of Saturn S-IC AERODYNAMIC engine gimbal forces and base pressures using a cold-flow-jet simulation technique / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearing house for Federal Scientific and Technical Information, 1967), by Bernard J. Blaha, Donald L. Bresnahan, Robert A. Wasko, and Lewis Research Center (page images at HathiTrust)
Wind-tunnel investigation at Mach numbers from 0.60 to 1.20 of the static aerodynamic characteristics of a model of a possible nonlifting reentry capsule in combination with a rocket booster / (Washington D.C. : National Aeronautics and Space Administration, 1960), by Albin O. Pearson and Langley 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 / (Washington, D.C. : 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)
Low-speed measurements of oscillatory lateral stability derivatives of a model of 60° delta-wing bomber / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by John W. Paulson and Langley Research Center (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 / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Barbara J. Sort, Simon C. Sommer, and Ames Research Center (page images at HathiTrust)
Pressure measurements obtained in flight at transonic speeds for a conically cambered delta wing / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Earl R. Keener and Flight Research Center (U.S.) (page images at HathiTrust)
Research on blunt-faced entry configurations at angles of attack Between 60° and 90° / (Washington D.C. : National Aeronautics and Space Administration, 1960), by William H. Phillips and Langley Research Center (page images at HathiTrust)
Stability and control characteristics at a Mach number of 1.41 of a variable-sweep airplane configuration capable of low-level supersonic attack-outer wing swept 75°and 108° / (Washington D.C. : National Aeronautics and Space Administration, 1960), by Ross B. Robinson, Paul W. Howard, and Langley Research Center (page images at HathiTrust)
Effects of three spanwise twist variations on the longitudinal aerodynamic characteristics of a thin 45° sweptback highly tapered wing at transonic speeds / (Washington D.C. : National Aeronautics and Space Administration, 1959), by John P. Mugler and Langley Research Center (page images at HathiTrust)
Stability and control characteristics at low subsonic speeds of an airplane configuration having two types of variable-sweep wings / (Washington D.C. : National Aeronautics and Space Administration, 1960), by Bernard Spencer and Langley Research Center (page images at HathiTrust)
The transonic aerodynamic characteristics of two variable-sweep airplane configurations capable of low-level supersonic attack / (Washington D.C. : National Aeronautics and Space Administration, 1960), by Ralph P. Bielat, William J. Alford, A. Warner Robins, and Langley Research Center (page images at HathiTrust)
A free-flight investigation of the drag coefficients of two single-engine supersonic interceptor configurations from Mach number 0.8 to 1.90 to determine the effect of inlet and engine locations / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Joseph H. Judd, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
Acoustic environments of the F-111A aircraft during ground runup /, by John N. Cole, Justus F. Rose, and sponsor Aerospace Medical Research Laboratories (U.S.) (page images at HathiTrust)
Buffet characteristics of the model F-4 airplane in the transonic flight regime /, by Marshall Cohen, sponsor Air Force Flight Dynamics Laboratory (U.S.), sponsor McDonnell Aircraft Company, and issuing body United States. Air Force. Systems Command (page images at HathiTrust)
Flight propulsion control coupling for thrust vectoring fighter aircraft., by Frederick C. Glaser, sponsor Douglas Aircraft Company, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters., by Edsel R. Glasgow, D. A. Tappeiner, R. Posthumus, R. D. Grennan, R. A. Fox, Leonard D. Miller, Don M. Santman, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
Evaluation of the twin nozzle/afterbody drag and nozzle internal performance computer deck with ESIT free jet data /, by Phillip C. Everling, Douglas L. Bowers, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters., by Edsel R. Glasgow, T. J. Jones, T. E. Charbonneau, Leonard D. Miller, Don M. Santman, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters., by Edsel R. Glasgow, T. J. Jones, D. A. Tappeiner, T. E. Charbonneau, D. K. Hill, R. D. Grennan, R. A. Fox, D. A. Fox, Leonard D. Miller, Don M. Santman, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters., by Edsel R. Glasgow, D. K. Hill, R. D. Grennan, R. A. Fox, Leonard D. Miller, Don M. Santman, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
Flight investigation of fighter side-stick force-deflection characteristics /, by G. Warren Hall, Rogers E. Smith, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Analysis/Theory of controlled configured structures /, by J. G. Williams, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor LTV Aerospace Corporation (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters., by Edsel R. Glasgow, T. J. Jones, T. E. Charbonneau, Leonard D. Miller, Don M. Santman, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
Aircraft motion sensitivity to cross and cross-coupling damping derivatives /, by R. W. Butler, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
Aerodynamic characteristics and store loads of a 1/24-scale F-111 aircraft model with three external store loadings /, by C. F. Anderson, Inc.. sponsor ARO, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
A Wind tunnel test to study the mutual interference of multiple bodies in the flow field of the F-4C aircraft in the transonic speed range /, by A. A. Hesketh, Inc.. sponsor ARO, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
Pressure and static force test of three elliptic missile body configurations at mach numbers 1.5 to 5.0 /, by M. E. Sellers, L Siler, Air Force Wright Aeronautical Laboratories. sponsor, Calspan Field Services. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
Wind tunnel investigation of aerodynamic loads on weapons separated from carriage under the wing of a tactical fighter aircraft at supersonic speeds /, by J. C. Donaldson, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
Afterbody drag investigation of a twin-nozzle fighter-type model at Mach numbers from 0.6 to 1.5 /, by Earl A. Price, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
Final test report : X-29A Vortex Flow Control (VFC) flight test results /, by Frank Luria, Brian Hobbs, Paul Pellicano, Joseph Krumenacker, William Gillard, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and sponsor Grumman Aircraft Engineering Corporation (page images at HathiTrust)
Use of the flow angularity technique for predicting store separation trajectories /, by Stephen C. Korn, United States. Air Force. Systems Command. sponsor, and Air Force Armament Laboratory. issuing body (page images at HathiTrust)
Validation and expansion of the flow angularity technique for predicting store separation trajectories /, by Stephen C. Korn, United States. Air Force. Systems Command. sponsor, and Air Force Armament Laboratory. issuing body (page images at HathiTrust)
Pressure test of three elliptic missile body configuratins /, by Marvin E. Sellers, Calspan Corporation. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
An Experimental study of several wind tunnel wall configurations using two V/STOL model configurations /, by T. W. Binion, United States. Air Force. Arnold Air Force Base. sponsor, United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body, and Inc. sponsor ARO (page images at HathiTrust)
Static stability test of three elliptic missile body configurations /, by Marvin E. Sellers, Calspan Corporation. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)

Filed under: Cobra (Jet fighter plane)

Inlet performance characteristics of a 1/5 scale Northrop YF-17 model at transonic and supersonic Mach numbers /, by M. E. Sanders, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)

Filed under: Crusader (Jet fighter plane)

Extraction from flight data of longitudinal aerodynamic coefficients for F-8 aircraft with supercritical wing / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by James L. Williams, William T. Suit, and Langley Research Center (page images at HathiTrust)
Description and flight test results of the NASA F-8 digital fly-by-wire control system : a collection of papers from the NASA Symposium on Advanced Control Technology, Los Angeles, Calif., July 9-11, 1974. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Calif.) NASA Symposium on Advanced Control Technology (1974 : Los Angeles and Flight Research Center (U.S.) (page images at HathiTrust)
Extraction from flight data of lateral aerodynamic coefficients for F-8 aircraft with supercritical wing / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by James L. Williams, William T. Suit, and Langley Research Center (page images at HathiTrust)
Preliminary system design study for a digital fly-by-wire flight control system for an F-8C aircraft / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1976]), by C. L. Seacord, Darrel Vaughn, Langley Research Center, and Honeywell Inc (page images at HathiTrust)
Piloted simulation of an algorithm for onboard control of time-optimal intercept / (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 Douglas B. Price, Daniel D. Moerder, Anthony J. Calise, and Langley Research Center (page images at HathiTrust)
F-8C adaptive flight control extensions / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Günter Stein, Gary L. Hartmann, Honeywell Inc, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Lateral aerodynamic parameters extracted from light data for the F-8C airplane in maneuvering flight / (Washington : Natural Aeronautics and Space Administration : Springfield, Va. : For sale by the National Technical Information Service, 1977), by William T. Suit and United States National Aeronautics and Space Administration (page images at HathiTrust)

Filed under: Delta Dart (Jet fighter plane)

Wind-tunnel free-flight investigation of a 0.15-scale model of the F-106B airplane with vortex flaps / (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 Long P. Yip and Langley Research Center (page images at HathiTrust)
Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Roger Chamberlin and Lewis Research Center (page images at HathiTrust)
Flight investigation of installation effects on a plug nozzle with a series of boattailed primary shrouds installed on an underwing nacelle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Verlon L. Head and Lewis Research Center (page images at HathiTrust)
Flight velocity effects on the jet noise of several variations of a 104-tube suppressor nozzle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Richard R. Burley and Lewis Research Center (page images at HathiTrust)
Flight Reynolds number effects on a fighter-type, circular-arc - 19 ̊conic boattail nozzle at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Roger Chamberlin and Lewis Research Center (page images at HathiTrust)
Flight velocity effects on jet noise of several variations of a twelve-chute suppressor installed on a plug nozzle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Richard R. Burley, Albert L. Johns, and Lewis Research Center (page images at HathiTrust)
Flight velocity effects on jet noise of several variations of a 48-tube suppressor installed on a plug nozzle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Richard R. Burley, Verlon L. Head, and Lewis Research Center (page images at HathiTrust)
Operational performance of vapor-screen systems for in-flight visualization of leading-edge vortices on the F-106B aircraft / (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 John E. Lamar (page images at HathiTrust)

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