You limited your search to:

 Decade: 1940-1949
 Year: 1942
 Collection: National Advisory Committee for Aeronautics Collection
The effect of exhaust-stack shape on the design and performance of the individual cylinder exhaust-gas jet-propulsion system

The effect of exhaust-stack shape on the design and performance of the individual cylinder exhaust-gas jet-propulsion system

Date: November 1, 1942
Creator: Humble, Leroy V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Tests of Modifications to Improve the Aileron Control Characteristics of a North American XP-51 Airplane (AC No. 41-38)

Flight Tests of Modifications to Improve the Aileron Control Characteristics of a North American XP-51 Airplane (AC No. 41-38)

Date: June 1, 1942
Creator: Hoover, Herbert H.
Description: Investigations were undertaken to improve the ailerons of a P-51 fighter so as to obtain greater effectiveness without increasing the stick forces. Modifications consisted of increasing the deflection range of the aileron to 70 percent and changing the original concave section to a thick section with beveled trailing edge. Results of the modified ailerons showed an increase in effectiveness over the original aileron of 70 percent at low speed and 55 percent at high speeds.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Date: September 1, 1942
Creator: Baals, Donald D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On a new method for calculating the potential flow past a body of revolution

On a new method for calculating the potential flow past a body of revolution

Date: July 1, 1942
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method for calculating heat transfer in the laminar flow region of bodies

A method for calculating heat transfer in the laminar flow region of bodies

Date: December 1, 1942
Creator: Look, Bonne C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method for determining the rate of heat transfer from a wing or streamline body

A method for determining the rate of heat transfer from a wing or streamline body

Date: December 1, 1942
Creator: Mccullough, George B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flutter calculations in three degrees of freedom

Flutter calculations in three degrees of freedom

Date: January 1, 1942
Creator: Theodorsen, Theodore & Garrick, I E
Description: The present paper is a continuation of the general study of flutter published in NACA reports nos. 496 and 685. The paper is mainly devoted to flutter in three degrees of freedom (bending, torsion, and aileron) for which a number of selected cases have been calculated and presented in graphical form. The results are analyzed and discussed with regard to the effects of structural damping, of fractional-span ailerons, and of mass-balancing. The analysis shows that more emphasis should be put on the effect of structural damping and less on mass-balancing. The conclusion is drawn that a definite minimum amount of structural damping, which is usually found to be present, is essential in the calculations for an adequate description of the flutter case. Theoretical flutter predictions are thus brought into closer agreement with the facts of experience. A brief discussion is included of a particular biplane that had experienced flutter at about 200 miles per hour. Some simplifications have been achieved in the method of calculation. (author).
Contributing Partner: UNT Libraries Government Documents Department
Ground effect on downwash angles and wake location

Ground effect on downwash angles and wake location

Date: May 1, 1942
Creator: Katzoff, S & Sweberg, Harold H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Normal-pressure tests of circular plates with clamped edges

Normal-pressure tests of circular plates with clamped edges

Date: January 1, 1942
Creator: Mcpherson, Albert E; Ramberg, Walter & Levy, Samuel
Description: A fixture is described for making normal-pressure tests of flat plates 5 inches in diameter in which particular care was taken to obtain rigid clamping at the edges. Results are given for 19 plates, ranging in thickness from 0.015 to 0.072 inch. The center deflections and the extreme-fiber stresses at low pressures were found to agree with theoretical values; the center deflections at high pressures were 4 to 12 percent greater than the theoretical values. Empirical curves are derived of the pressure for the beginning of permanent set as a function of the dimensions of the plate and the tensile properties of the material.
Contributing Partner: UNT Libraries Government Documents Department
Square plate with clamped edges under normal pressure producing large deflections

Square plate with clamped edges under normal pressure producing large deflections

Date: January 1, 1942
Creator: Levy, Samuel
Description: A theoretical analysis is given for the stresses and deflections of a square plate with clamped edges under normal pressure producing large deflections. Values of the bending stress and membrane stress at the center of the plate and at the midpoint of the edge are given for center deflections up to 1.9 times the plate thickness. The shape of the deflected surface is given for low pressures and for the highest pressure considered. Convergence of the solution is considered and it is estimated that the possible error is less than 2 percent. The results are compared with the only previous approximate analysis known to the author and agree within 5 percent. They are also shown to compare favorably with the known exact solutions for the long rectangular plate and the circular plate.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST