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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1952
 Collection: Technical Report Archive and Image Library
Abnormal grain growth in S-816 alloy

Abnormal grain growth in S-816 alloy

Date: April 1952
Creator: Rush, A I; Freeman, J W & White, A E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accuracy of approximate methods for predicting pressures on pointed nonlifting bodies of revolution in supersonic flow

Accuracy of approximate methods for predicting pressures on pointed nonlifting bodies of revolution in supersonic flow

Date: August 1952
Creator: Ehret, Dorris M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Achievement of continuous wall curvature in design of two-dimensional symmetrical supersonic nozzles

Achievement of continuous wall curvature in design of two-dimensional symmetrical supersonic nozzles

Date: January 1952
Creator: Evvard, J C & Marcus, Lawrence R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An active particle diffusion theory of flame quenching for laminar flames / Dorothy M. Simon and Frank E. Belles

An active particle diffusion theory of flame quenching for laminar flames / Dorothy M. Simon and Frank E. Belles

Date: March 4, 1952
Creator: Simon, Dorothy M & Belles, Frank E
Description: An equation for quenching distance based on the destruction of chain carriers by the surface is derived. The equation expresses the quenching distance in terms of the diffusion coefficients and partial pressures of the chain carriers and gas phase molecules, the efficiency of the surface as a chain breaker, the total pressure of the mixture, and a constant which depends on the geometry of the quenching surface. Quenching distances measured by flashback for propane-air flames are shown to be consistent with the mechanism. The derived equation is used with the lean inflammability limit and a rate constant calculated from burning velocity data to estimate quenching distances for propane-air (hydrocarbon lean) flames satisfactorily.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 2.01 of nacelle shape and position on the aerodynamic characteristics in

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 2.01 of nacelle shape and position on the aerodynamic characteristics in

Date: July 25, 1952
Creator: Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch

Date: January 10, 1952
Creator: Driver, Cornelius & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the static lateral stability characteris

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the static lateral stability characteris

Date: August 1, 1952
Creator: Hamilton, Clyde V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance : transonic-bump method

Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance : transonic-bump method

Date: September 16, 1952
Creator: Wiley, Harleth G & Zontek, Leon
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a full-span flap type of control with overhang balance : transonic-bump method

Aerodynamic characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a full-span flap type of control with overhang balance : transonic-bump method

Date: January 25, 1952
Creator: Lockwood, Vernard E & Hagerman, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.

Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.

Date: January 15, 1952
Creator: Morrison, William D , Jr & Fournier, Paul G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degrees sweptback, aspect-ratio-4 tail surface deflected about a skewed hinge axis

The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degrees sweptback, aspect-ratio-4 tail surface deflected about a skewed hinge axis

Date: July 3, 1952
Creator: Hammond, Alexander D & Watson, James M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing

Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing

Date: November 18, 1952
Creator: Wiley, Harleth G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes

Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes

Date: June 1, 1952
Creator: Riebe, John M & Naeseth, Rodger L
Description: An investigation was made in the Langley 300-mph 7- by 10-foot tunnel to determine the aerodynamic characteristics of a refined deep-step planing-tail hull with various forebody and afterbody shapes and, for comparison, a streamline body simulating the fuselage of a modern transport airplane. The results of the tests indicated that the configurations incorporating a forebody with a length-beam ratio of 7 had lower minimum drag coefficients than the configurations incorporating a forebody with length-beam ratio of 5. The lowest minimum drag coefficients, which were considerably less than that of a conventional hull and slightly less than that of a streamline body, were obtained on the length-beam-ratio-7 forebody, alone and with round center boom. Drag coefficients and longitudinal- and lateral-stability parameters presented include the interference of a 21-percent-thick support wing.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Date: April 11, 1952
Creator: Spearman, M Leroy & Robinson, Ross B
Description: A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and tunnel tests are presented and, where possible, are supplemented by empirical and theoretical calculations.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of three deep-step planing-tail flying-boat hulls and a transverse-step hull with extended afterbody

Aerodynamic characteristics of three deep-step planing-tail flying-boat hulls and a transverse-step hull with extended afterbody

Date: August 1, 1952
Creator: Riebe, John M & Naeseth, Rodger L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Date: July 22, 1952
Creator: Boyd, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two delta wings at Mach number 4.04 and correlations of lift and minimum-drag data for delta wings at Mach numbers from 1.62 to 6.9

Aerodynamic characteristics of two delta wings at Mach number 4.04 and correlations of lift and minimum-drag data for delta wings at Mach numbers from 1.62 to 6.9

Date: December 23, 1952
Creator: Ulmann, Edward F & Dunning, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump

Aerodynamic characteristics of two-plane, unswept tapered wings of aspect ratio 3 and 3-percent thickness from tests on a transonic bump

Date: May 2, 1952
Creator: Emerson, Horace F & Gale, Bernard M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section

The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section

Date: June 1, 1952
Creator: Beckwith, Ivan E; Ridyard, Herbert W & Cromer, Nancy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic design of supersonic propellers from structural considerations

The aerodynamic design of supersonic propellers from structural considerations

Date: December 1, 1952
Creator: Hammack, Jerome B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic load measurements over a leading-edge slat on a 40 degree sweptback wing at Mach numbers from 0.10 to 0.91

Aerodynamic load measurements over a leading-edge slat on a 40 degree sweptback wing at Mach numbers from 0.10 to 0.91

Date: September 23, 1952
Creator: Cahill, Jones F & Nuber, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic loading characteristics of a wing-fuselage combination having a wing of 45 degrees sweepback measured in the Langley 8-foot transonic tunnel

Aerodynamic loading characteristics of a wing-fuselage combination having a wing of 45 degrees sweepback measured in the Langley 8-foot transonic tunnel

Date: May 19, 1952
Creator: Loving, Donald L & Williams, Claude V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) II : aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) II : aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies

Date: May 8, 1952
Creator: Jack, John R & Gould, Lawrence I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical characteristics of a 45 degree sweptback wing-fuselage combination and the fuselage alone obtained in the Langley 8-foot transonic tunnel

Aeronautical characteristics of a 45 degree sweptback wing-fuselage combination and the fuselage alone obtained in the Langley 8-foot transonic tunnel

Date: September 16, 1952
Creator: Osborne, Robert S & Mugler John P , JR
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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