The Online Books Page

Jet fighter planes

See also what's at your library, or elsewhere.

Broader terms:

Narrower terms:

Used for:

Fighter jet planes

Filed under: Jet fighter planes

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 (National Advisory Committee for Aeronautics, 1955), by Joseph H. Judd, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Acoustic environments of the F-111A aircraft during ground runup (Wright-Patterson Air Force Base, Ohio : Aerospace Medical Research Laboratories, Aerospace Medical Division, Air Force Systems Command, United States Air Force, 1968., 1968), by John N. Cole, Justus F. Rose, and Aerospace Medical Research Laboratories (U.S.) (page images at HathiTrust)
Flight investigation of fighter side-stick force-deflection characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1975., 1975), by G. Warren Hall, Rogers E. Smith, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Aircraft motion sensitivity to cross and cross-coupling damping derivatives (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by R. W. Butler, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Afterbody drag investigation of a twin-nozzle fighter-type model at Mach numbers from 0.6 to 1.5 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by Earl A. Price, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)

Filed under: Jet fighter planes -- Computer programs

Integrated airframe - nozzle performance for designing twin-engine fighters. Volume VI, Revised operating manual for twin nozzle/afterbody drag and nozzle internal performance computer deck (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), by Edsel R. Glasgow, D. A. Tappeiner, R. Posthumus, R. D. Grennan, R. A. Fox, Leonard D. Miller, Don M. Santman, Air Force Flight Dynamics Laboratory (U.S.), and 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 (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, 1974., 1974), by Phillip C. Everling, Douglas L. Bowers, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters. Volume V, Operating manual for supersonic axisymmetric nozzle boattail drag computer deck (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), by Edsel R. Glasgow, T. J. Jones, T. E. Charbonneau, Leonard D. Miller, Don M. Santman, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-California Company (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters. Volume IV, Operating manual for subsonic axisymmetric nozzle boattail drag computer deck (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), by Edsel R. Glasgow, T. J. Jones, T. E. Charbonneau, Leonard D. Miller, Don M. Santman, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-California Company (page images at HathiTrust)

Filed under: Jet fighter planes -- Design and construction

Integrated airframe - nozzle performance for designing twin-engine fighters. Volume I (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), by Edsel R. Glasgow, D. K. Hill, R. D. Grennan, R. A. Fox, Leonard D. Miller, Don M. Santman, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-California Company (page images at HathiTrust)
Analysis/Theory of controlled configured structures (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by J. G. Williams, Air Force Flight Dynamics Laboratory (U.S.), and LTV Aerospace Corporation (page images at HathiTrust)
Flight propulsion control coupling for thrust vectoring fighter aircraft. Volume III, Phase II (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1980., 1980), by Frederick C. Glaser, Douglas Aircraft Company, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)

Filed under: Jet fighter planes -- Testing

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)

Filed under: Jet fighter planes -- Wind tunnel testing

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)
Low-speed measurements of oscillatory lateral stability derivatives of a model of 60 degree delta-wing bomber (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 equals 4 (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 (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° (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 degree and 108 degree (National Aeronautics and Space Administration, 1960), by Ross B. Robinson, Paul W. Howard, and Langley Research Center (page images at HathiTrust)
Wind-tunnel investigation of Saturn S-IC AERODYNAMIC engine gimbal forces and base pressures using a cold-flow-jet simulation technique (National Aeronautics and Space Administration ;, 1967), by Bernard J. Blaha, Donald L. Bresnahan, Robert A. Wasko, and Lewis Research Center (page images at HathiTrust)
Effects of 3 spanwise twist variations on the longitudinal aerodynamic characteristics of a thin 45 degree sweptback highly tapered wing at transonic speeds (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 (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 (National Aeronautics and Space Administration, 1960), by Ralph P. Bielat, William J. Alford, A. Warner Robins, and Langley 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 (National Aeronautics and Space Administration, 1960), by Albin O. Pearson and Langley Research Center (page images at HathiTrust)
Integrated airframe - nozzle performance for designing twin-engine fighters. Volume II, Wind tunnel data identification and presentation (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), 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, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-California Company (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 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by J. C. Donaldson, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Pressure test of three elliptic missile body configuratins (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1985., 1985), by Marvin E. Sellers, Calspan Corporation, and Arnold Engineering Development Center (page images at HathiTrust)
Aerodynamic characteristics and store loads of a 1/24-scale F-111 aircraft model with three external store loadings (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by C. F. Anderson, Inc ARO, and Arnold Engineering Development Center (page images at HathiTrust)
An Experimental study of several wind tunnel wall configurations using two V/STOL model configurations (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1975., 1975), by T. W. Binion, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Use of the flow angularity technique for predicting store separation trajectories (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Product Assurance Division, Air Force Systems Command, United States Air Force, 1971., 1971), by Stephen C. Korn, United States. Air Force. Systems Command, and Air Force Armament Laboratory (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 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1979., 1979), by A. A. Hesketh, Inc ARO, and Arnold Engineering Development Center (page images at HathiTrust)
Validation and expansion of the flow angularity technique for predicting store separation trajectories (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Aircraft Compatibility and Weapons Flight Dynamics Branch, Product Assurance Division, Air Force Systems Command, United States Air Force, 1972., 1972), by Stephen C. Korn, United States. Air Force. Systems Command, and Air Force Armament Laboratory (page images at HathiTrust)
Pressure and static force test of three elliptic missile body configurations at mach numbers 1.5 to 5.0 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1983., 1983), by M. E. Sellers, L Siler, Air Force Wright Aeronautical Laboratories, Calspan Field Services, and Arnold Engineering Development Center (page images at HathiTrust)
Static stability test of three elliptic missile body configurations (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1985., 1985), by Marvin E. Sellers, Calspan Corporation, and Arnold Engineering Development Center (page images at HathiTrust)
Results of wind tunnel tests on two Navy AERCAB vehicles (Warminster, Pennsylvania : Naval Air Development Center, Aero Mechanics Department, 1971., 1971), by Daniel Scharf and Naval Air Development Center (page images at HathiTrust)
Advanced Fighter Technology Integration (AFTI) Phase I. Volume II Part II, Appendix I, Phase I wind tunnel data summary (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1975., 1975), by Gordon Rosenthal, Air Force Flight Dynamics Laboratory (U.S.), and Air Force Wright Aeronautical Laboratories (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 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1974., 1974), by M. E. Sanders, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)

Filed under: Crusader (Jet fighter plane)

Preliminary system design study for a digital fly-by-wire flight control system for an F-8C aircraft (National Aeronautics and Space Administration ;, 1976), by C. L. Seacord, Darrel Vaughn, Langley Research Center, and Honeywell Inc (page images at HathiTrust)
F-8C adaptive flight control extensions (National Aeronautics and Space Administration ;, 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 (Natural Aeronautics and Space Administration :, 1977), by William T. Suit and United States National Aeronautics and Space Administration (page images at HathiTrust)
Extraction from flight data of lateral aerodynamic coefficients for F-8 aircraft with supercritical wing (National Aeronautics and Space Administration ;, 1974), by James L. Williams, William T. Suit, and Langley Research Center (page images at HathiTrust)
Extraction from flight data of longitudinal aerodynamic coefficients for F-8 aircraft with supercritical wing (National Aeronautics and Space Administration ;, 1974), by James L. Williams, William T. Suit, and Langley Research Center (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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by John E. Lamar (page images at HathiTrust)
F-106 Delta Dart : AMC Museum (Dover Air Force Base, Del.). ([AMC Museum?], 2004), by United States Air Force (page images at HathiTrust)

More items available under narrower terms.

Help with reading books -- Report a bad link -- Suggest a new listing

Home -- Search -- New Listings -- Authors -- Titles -- Subjects -- Serials

Books -- News -- Features -- Archives -- The Inside Story

Edited by John Mark Ockerbloom (onlinebooks@pobox.upenn.edu)
OBP copyrights and licenses.