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 Decade: 1940-1949
 Year: 1943
 Collection: National Advisory Committee for Aeronautics Collection
Determination of general relations for the behavior of turbulent boundary layers

Determination of general relations for the behavior of turbulent boundary layers

Date: July 1, 1943
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of general relations for the behavior of turbulent boundary layers

Determination of general relations for the behavior of turbulent boundary layers

Date: January 1, 1943
Creator: Von Doenhoff, Albert E & Tetervin, Neal
Description: An analysis has been made of a considerable amount of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. It was found that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter. This parameter was chosen as the ratio of the displacement thickness to the momentum thickness of the boundary layer. The variables that control the development of the turbulent boundary layer apparently are: (1) the ratio of the nondimensional pressure gradient, expressed in terms of the local dynamic pressure outside the boundary layer and boundary-layer thickness, to the local skin-friction coefficient and (2) the shape of the boundary layer. An empirical equation has been developed in terms of these variables that, when used with the momentum equation and the skin-friction relation, makes it possible to trace the development of the turbulent boundary layer to the separation point.
Contributing Partner: UNT Libraries Government Documents Department
Determination of the damping moment in yawing for tapered wings with partial-span flaps

Determination of the damping moment in yawing for tapered wings with partial-span flaps

Date: August 1, 1943
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of the Mass Moments and Radii of Inertia of the Sections of a Tapered Wing and the Center-of-Gravity Line along the Wing Span

Determination of the Mass Moments and Radii of Inertia of the Sections of a Tapered Wing and the Center-of-Gravity Line along the Wing Span

Date: December 1, 1943
Creator: Savelyev, V. V.
Description: For computing the critical flutter velocity of a wing among the data required are the position of the line of centers of gravity of the wing sections along the span and the mass moments and radii of inertia of any section of the wing about the axis passing through the center of gravity of the section. A sufficiently detailed computation of these magnitudes even if the weights of all the wing elements are known, requires a great deal of time expenditure. Thus a rapid competent worker would require from 70 to 100 hours for the preceding computations for one wing only, while hundreds of hours would be required if all the weights were included. With the aid of the formulas derived in the present paper, the preceding work can be performed with a degree of accuracy sufficient for practical purposes in from one to two hours, the only required data being the geometric dimensions of the outer wing (tapered part), the position of its longerons, the total weight of the outer wing, and the approximate weight of the longerons, The entire material presented in this paper is applicable mainly to wings of longeron construction of the CAHI type and investigations ...
Contributing Partner: UNT Libraries Government Documents Department
Development of thermal ice-prevention equipment for the B-17F airplane

Development of thermal ice-prevention equipment for the B-17F airplane

Date: August 1, 1943
Creator: Rodert, Lewis A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of thermal ice-prevention equipment for the B-24D airplane

Development of thermal ice-prevention equipment for the B-24D airplane

Date: February 1, 1943
Creator: Rodert, Lewis A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Ditching tests with 1/10-size model of the Army A-20A airplane I : calm-water tests in NACA tank no.2

Ditching tests with 1/10-size model of the Army A-20A airplane I : calm-water tests in NACA tank no.2

Date: November 1, 1943
Creator: Jarvis, George A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag Measurements of a Protruding.50-Caliber Machine Gun with Barrel Jacket Removed

Drag Measurements of a Protruding.50-Caliber Machine Gun with Barrel Jacket Removed

Date: January 1, 1943
Creator: Luoma, Arvo A.
Description: Tests were made in 8-ft high-speed wind tunnel to determine the drag reduction possible by eliminating the barrel jacket of a protruding 50-caliber aircraft gun. It was found that the drag of a standard aircraft gun protruding into the air stream at right angles to the flow can be reduced by 23% by discarding the barrel jacket. At 300 mph and sea-level conditions, this amounts to a decrease in drag of from 83 to 64 pounds. A rough surface finish on the barrel was found to have no adverse effects on the drag of the barrel, the drag being actually less at high Mach Numbers.
Contributing Partner: UNT Libraries Government Documents Department
The effect of altitude on bomber performance

The effect of altitude on bomber performance

Date: October 1, 1943
Creator: Crigler, John L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of altitude on cooling

The effect of altitude on cooling

Date: March 1, 1943
Creator: Wood, George P
Description: None
Contributing Partner: UNT Libraries Government Documents Department