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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
The effect of amphibious floats on the power-off stability and control characteristics of a twin-engine cargo airplane

The effect of amphibious floats on the power-off stability and control characteristics of a twin-engine cargo airplane

Date: January 18, 1943
Creator: Jackson, Roy P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Artificial Aging on the Tensile Properties of Alclad 24S-T and 24S-T Aluminum Alloy

The Effect of Artificial Aging on the Tensile Properties of Alclad 24S-T and 24S-T Aluminum Alloy

Date: August 1, 1943
Creator: Kotanchik, Joseph N.; Woods, Walter & Zender, George W.
Description: An experimental study was made to determine the effect of artificial aging on the tensile properties of alclad 24S-T and 24S-T aluminum-alloy sheet material. The results of the tests show that certain combinations of aging time and temperature cause a marked increase in the yield strength and a small increase in the ultimate strength; these increases are accompanied by a very large decrease in elongation. A curve is presented that shows the maximum yield strengths that can be obtained by aging this material at various combinations of time and temperature. The higher values of yield stress are obtained in material aged at relatively longer times and lower temperatures.
Contributing Partner: UNT Libraries Government Documents Department
Effect of carburetor-mixture-control and supercharger characteristics on fuel knock under simulated sea-level flight conditions

Effect of carburetor-mixture-control and supercharger characteristics on fuel knock under simulated sea-level flight conditions

Date: March 1, 1943
Creator: Wear, Jerrold D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

Date: January 1, 1943
Creator: Allen, H. Julian & Nitzberg, Gerald E.
Description: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It i s shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients . The available data indicate that for low-drag and high critical compressibility speed airfoils and bodies of revolution, this effect is favorable.
Contributing Partner: UNT Libraries Government Documents Department
The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

Date: January 1, 1943
Creator: Nitzberg, Gerald E
Description: Summary: The effective change in the velocity of flow past a wing section, caused by the presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. It is shown that for a symmetrical section at zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M^2 to take account of compressibility effects. The Mach number, M, corresponds to conditions in the wind-tunnel test section with the model removed (p. 1.).
Contributing Partner: UNT Libraries Government Documents Department
The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem

The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem

Date: June 1, 1943
Creator: Klein, Milton M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of exhaust back pressure on engine power

Effect of exhaust back pressure on engine power

Date: June 1, 1943
Creator: Pinkel, Benjamin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fillers and of mixing procedure on the strength of plastic materials

Effect of fillers and of mixing procedure on the strength of plastic materials

Date: January 1, 1943
Creator: Kynoch, William & Patronsky, L A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of inlet-valve design, size, and lift on the air capacity and output of a four-stroke engine

The effect of inlet-valve design, size, and lift on the air capacity and output of a four-stroke engine

Date: November 1, 1943
Creator: Livengood, James C & Stanitz, John D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of length-beam ration on resistance and spray of three models of flying-boat hulls

Effect of length-beam ration on resistance and spray of three models of flying-boat hulls

Date: October 1, 1943
Creator: Zeck, Howard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel

The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel

Date: August 1, 1943
Creator: Seacord, Charles L & Campbell, John P.
Description: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions.
Contributing Partner: UNT Libraries Government Documents Department
The effect of mass distribution on the lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

The effect of mass distribution on the lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

Date: January 1, 1943
Creator: Campbell, John P & Seacord, Charles L , Jr
Description: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing moments of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet

Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet

Date: January 1, 1943
Creator: Rafel, Norman
Description: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
Contributing Partner: UNT Libraries Government Documents Department
Effect of pH on strength of resin bonds

Effect of pH on strength of resin bonds

Date: October 1, 1943
Creator: Kline, G. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department