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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1950
 Collection: Technical Report Archive and Image Library
4-Channel Line Driver: Modified

4-Channel Line Driver: Modified

Date: 1950?
Creator: Titterton, E. W.
Description: Technical drawing of line drivers and amplifiers for use in nuclear reactors.
Contributing Partner: UNT Libraries Government Documents Department
An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2

An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2

Date: February 23, 1950
Creator: Ritchie, Virgil S; Wright, Ray H & Tulin, Marshall P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
30 Rv. Power Supply

30 Rv. Power Supply

Date: 1950?
Creator: U.S. Atomic Energy Commission
Description: Technical drawing of electronic circuits and power supplies to nuclear reactors.
Contributing Partner: UNT Libraries Government Documents Department
Ability of pilots to control simulated short-period yawing oscillations

Ability of pilots to control simulated short-period yawing oscillations

Date: November 13, 1950
Creator: Phillips, William H & Cheatham, Donald C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method

Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method

Date: May 5, 1950
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: May 5, 1950
Creator: Hall, Albert W & Morris, Garland J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: October 10, 1950
Creator: Kemp, William B , Jr; Goodson, Kenneth W & Booth, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Date: April 1950
Creator: Smith, Hamilton A & Schaefer, Raymond F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A009 airfoil section

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A009 airfoil section

Date: April 6, 1950
Creator: Spreemann, Kenneth P; Morrison, William D , Jr & Pasteur, Thomas B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: February 24, 1950
Creator: Myers, Boyd C , II & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: March 8, 1950
Creator: Polhamus, Edward C & Campbell, George S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: May 8, 1950
Creator: Myers, Boyd C , II & Wiggins, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of damping screens

Aerodynamic characteristics of damping screens

Date: January 1950
Creator: Schubauer, G B; Spangenberg, W G & Klebanoff, P S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 I : presentation and analysis of pressure measurements (stabilizing fins removed)

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 I : presentation and analysis of pressure measurements (stabilizing fins removed)

Date: July 20, 1950
Creator: Luidens, Roger W & Simon, Paul C
Description: Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle of attack and angle of attack except over the aft leeward side of body. At angle of attack, pitot pressure measurements in plane of model base indicated a pair of symmetrically disposed vortices on leeward side of body.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 II : presentation and analysis of force measurements

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 II : presentation and analysis of force measurements

Date: July 21, 1950
Creator: Esenwein, Fred T; Obery, Leonard J & Schueller, Carl F
Description: Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. III : analysis of force distribution at angle of attack (stabilizing fins removed)

Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. III : analysis of force distribution at angle of attack (stabilizing fins removed)

Date: December 12, 1950
Creator: Luidens, Roger W & Simon, Paul C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds

Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds

Date: May 2, 1950
Creator: Polhamus, Edward C & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Date: October 1950
Creator: Turner, M J & Rabinowitz, S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Date: September 1950
Creator: Stone, Ralph W , Jr; Burk, Sanger M , Jr & Bihrle, William, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic forces on slender plane- and cruciform-wing and body combinations

The aerodynamic forces on slender plane- and cruciform-wing and body combinations

Date: 1950?~
Creator: Spreiter, John R
Description: The load distribution, forces, and moments are calculated theoretically for inclined slender wing-body combinations consisting of a slender body of revolution and either a plane or cruciform arrangement of low-aspect-ratio pointed wings. The results are applicable at subsonic and transonic speeds, and at supersonic speeds, provided the entire wing-body combination lies near the center of the Mach cone.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: February 8, 1950
Creator: Love, Eugene S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: October 9, 1950
Creator: Heitmeyer, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: September 29, 1950
Creator: Lessing, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: May 8, 1950
Creator: Olson, Robert N & Mead, Merrill H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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