UNT Libraries Government Documents Department - 353 Matching Results

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Primary view of An 8-Foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers Up to 0.99 and for a Supersonic Mach Number of 1.2
Ritchie, Virgil S.; Wright, Ray H. & Tulin, Marshall P.
February 23, 1950
Primary view of Ability of Pilots to Control Simulated Short-Period Yawing Oscillations
Phillips, William H. & Cheatham, Donald C.
November 13, 1950
Primary view of Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method
Lockwood, Vernard E.
May 5, 1950
Primary view of Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections
Hall, Albert W. & Morris, Garland J.
May 5, 1950
Primary view of Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees
Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
October 10, 1950
Primary view of Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
Myers, Boyd C., II & King, Thomas J., Jr.
February 24, 1950
Primary view of Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section: transonic-bump method
Polhamus, Edward C. & Campbell, George S.
March 8, 1950
Primary view of Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section: Transonic-bump method
Myers, Boyd C., II & Wiggins, James W.
May 8, 1950
Primary view of Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)
Luidens, Roger W. & Simon, Paul C.
July 20, 1950
Primary view of Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements
Esenwein, Fred T.; Obery, Leonard J. & Schueller, Carl F.
July 21, 1950
Primary view of Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. 3: analysis of force distribution at angle of attack (stabilizing fins removed)
Luidens, Roger W. & Simon, Paul C.
December 12, 1950
Primary view of Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds
Polhamus, Edward C. & King, Thomas J., Jr.
May 2, 1950
Primary view of Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base
Love, Eugene S.
February 8, 1950
Primary view of Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load
Heitmeyer, John C.
October 9, 1950
Primary view of Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of sideslip on aerodynamic characteristics at a Mach number of 1.4 with the wing twisted and cambered
Lessing, Henry C.
September 29, 1950
Primary view of Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds
Olson, Robert N. & Mead, Merrill H.
May 8, 1950
Primary view of Aeronautical study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at supersonic speeds of a model with the wing twisted and cambered for uniform load
Hall, Charles F. & Heitmeyer, John C.
January 9, 1950
Primary view of Altitude-Chamber Performance of British Roll-Royce Nene II Engine 4: Effect of Operational Variables on Temperature Distribution at Combustion-Chamber Outlets
Huntley, Sidney C.
July 3, 1950
Primary view of Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 3 - 18.00-Inch-Diameter Jet Nozzle
Grey, Ralph E.; Brightwell, Virginia L. & Barson, Zelmar
July 10, 1950
Primary view of Altitude investigation of performance of turbine-propeller engine and its components
Wallner, Lewis E. & Saari, Martin J.
October 5, 1950
Primary view of Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine
Golladay, Richard L. & Bloomer, Harry E.
April 28, 1950
Primary view of Altitude Performance Characteristics of Tail-Pipe Burner With Converging Conical Burner Section on J47 Turbojet Engine
Prince, William R. & McAulay, John E.
December 19, 1950
Primary view of Altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzle
Jansen, Emmert T. & Thorman, H. Carl
August 11, 1950
Primary view of Altitude performance characteristics of turbojet-engine tail-pipe burner with variable-area exhaust nozzle using several fuel systems and flame holders
Johnson, LaVern A. & Meyer, Carl L.
December 29, 1950
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