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 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
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
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 1942
Creator: Baals, Donald D
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
The photoviscous properties of fluids

The photoviscous properties of fluids

Date: February 1, 1942
Creator: Weller, R; Hiddlehurst, D J & Steiner, R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of range of stress and of special notches on fatigue properties of aluminum alloys suitable for airplane propellers

Effects of range of stress and of special notches on fatigue properties of aluminum alloys suitable for airplane propellers

Date: June 1, 1942
Creator: Dolan, Thomas J
Description: Laboratory tests were made to obtain information on the load-resisting properties of X76S-T aluminum alloy when subjected to static, impact, and repeated loads. Results are presented from static-load test of unnotched specimens in tension and in torsion and of notched specimens in tension. Charpy impact values obtained from bend tests on notched specimens and tension impact values for both notched and unnotched specimens tested at several different temperatures are included. The endurance limits obtained from repeated bending fatigue tests made on three different types of testing machine are given for unnotched polished specimens, and the endurance limits of notched specimens subjected to six different ranges of bending stress are also reported. The results indicated that: (a) polished rectangular specimens had an endurance limit about 30 percent less than that obtained for round specimens; (b) a comparison of endurance limits obtained from tests on three different types of machine indicated that there was no apparent effect of speed of testing on the endurance limit for the range of speeds used (1,750 to 13,000 rpm). (c) the fatigue strength (endurance limit) of the X76S-T alloy was greatly decreased by the presence of a notch in the specimens; (d) no complete fractures of ...
Contributing Partner: UNT Libraries Government Documents Department
The influence of impact velocity on the tensile characteristics of some aircraft metals and alloys

The influence of impact velocity on the tensile characteristics of some aircraft metals and alloys

Date: October 1, 1942
Creator: Clark, Donald S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The electrical structure of thunderstorms

The electrical structure of thunderstorms

Date: November 1, 1942
Creator: Workman, E J; Helzer, R E & Pelsor, G T
Description: The time histories of thunderstorm charge distribution during three storms occurring during the summer of 1940 in the vicinity of the Albuquerque Airport were investigated by the use of eight synchronized recording electrometers arranged in a particular pattern over a field 1.6 kilometers above sea level.
Contributing Partner: UNT Libraries Government Documents Department
Stability of elastically supported columns

Stability of elastically supported columns

Date: March 23, 1942
Creator: Niles, Alfred S & Viscovich, Steven J
Description: A criterion is developed for the stiffness required of elastic lateral supports at the ends of a compression member to provide stability. A method based on this criterion is then developed for checking the stability of a continuous beam-column. A related method is also developed for checking the stability of a member of a pin-jointed truss against rotation in the plane of the truss.
Contributing Partner: UNT Libraries Government Documents Department
Beam and torsion tests of aluminum-alloy 615-T tubing

Beam and torsion tests of aluminum-alloy 615-T tubing

Date: October 1, 1942
Creator: Moore, R L & Holt, Marshall
Description: Tests were made to determine the effect of length and the effect of ratios of diameter to wall thickness upon the flexural and torsional moduli of failure of 61S-T aluminum-alloy tubing. The moduli of failure in bending, as determined by tests in which the tubing was loaded on the neutral axis at the one-third points of the span, were found to bear an approximately linear relationship with diameter-thickness ratio and were practically independent of span within the limits investigated. Empirical equations are given describing the relations obtained. The moduli of failure in torsion were found to be dependent upon length as well as upon diameter-thickness ratios. Empirical equations are given for predicting strengths within the range of plastic buckling. Within the elastic range, available torsion theories were found to be satisfactory.
Contributing Partner: UNT Libraries Government Documents Department
Bending with large deflection of a clamped rectangular plate with length-width ratio of 1.5 under normal pressure

Bending with large deflection of a clamped rectangular plate with length-width ratio of 1.5 under normal pressure

Date: April 14, 1942
Creator: Levy, Samuel & Greenman, Samuel
Description: The Von Karman equations for a thin flat plate with large deflections are solved for the special case of a plate with clamped edges having a ratio of length to width of 1.5 and loaded by uniform normal pressure. Center deflections, membrane stresses, and extreme-fiber bending stresses are given as a function of pressure for center deflections up to twice the thickness of the plate. For small deflections the results coincide with those obtained by Hencky from the linear theory. The maximum stresses and center deflection at high pressures differ less than 3 percent from those derived by Bostnov for an infinitely long plate with clamped edges. This agreement suggests that clamped plates with a length-to-width ratio greater than 1.5 may be reared as infinitely long plates for purposes of design.
Contributing Partner: UNT Libraries Government Documents Department
Bending tests of a monocoque box

Bending tests of a monocoque box

Date: January 1, 1942
Creator: Mcpherson, Albert E; Ramberg, Walter & Levy, Samuel
Description: A monocoque box beam consisting of a 24S-T aluminum-alloy sheet reinforced by four bulkheads and by longitudinal stringers and corner posts was subjected to bending loads as follows: pure bending about the lift axis, cantilever bending about the lift axis, and pure bending about both lift and drag axis. Longitudinal strains were measured for loads up to a load at which permanent set became measurable. The loads were sufficient to produce buckling of the sheet between stringers on the compression side of the box. The only noticeable effect of this buckling was a small increase in extreme-fiber strain on the compression side. The measured strains and measured deflections differed less than 10 percent from those computed from the simple beam theory after taking account of the effective width of the buckled sheet. The effect of the bulkheads on the distribution of stringer strain was negligible.
Contributing Partner: UNT Libraries Government Documents Department
Effect of normal pressure on the critical compressive stress of curved sheet

Effect of normal pressure on the critical compressive stress of curved sheet

Date: August 25, 1942
Creator: Rafel, Norman
Description: Results are presented of tests of two specimens tested to study the effect of normal pressure on the critical compressive stress for thin curved sheets. These specimens are designated by their respective rib spacings of 10 inches and 30 inches. The relationship between compressive stress and normal pressure at which buckles disappeared is independent of whether the buckles were made to disappear by increase of normal pressure or decrease of compressive stress. (author).
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (27th).administrative report including Technical Report nos. 704 to 726

Annual report of the National Advisory Committee for Aeronautics (27th).administrative report including Technical Report nos. 704 to 726

Date: 1942
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
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: June 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: May 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
The cross-flow plate-type intercooler

The cross-flow plate-type intercooler

Date: April 1, 1942
Creator: Valerino, Michael F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Construction of finned aluminum muffs for aircraft engine cylinder barrels

Construction of finned aluminum muffs for aircraft engine cylinder barrels

Date: April 1, 1942
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of additions of aromatics on the knocking characteristics of several 100-octane fuels at two engine speeds

Effect of additions of aromatics on the knocking characteristics of several 100-octane fuels at two engine speeds

Date: May 1, 1942
Creator: Harries, Myron L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of an aromatic mixture added to two 100-octane fuels on engine temperatures and fuel consumption

Effect of an aromatic mixture added to two 100-octane fuels on engine temperatures and fuel consumption

Date: June 1, 1942
Creator: Jones, Anthony W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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