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 Decade: 1940-1949
 Year: 1943
 Collection: National Advisory Committee for Aeronautics Collection
Analysis of the High-Altitude Cooling of the Ranger SGV-770 D-4 Engine in the Bell XP-77 Airplane

Analysis of the High-Altitude Cooling of the Ranger SGV-770 D-4 Engine in the Bell XP-77 Airplane

Date: October 1, 1943
Creator: Nielsen, Jack N. & Schumacher, Lloyd E.
Description: No abstract available.
Contributing Partner: UNT Libraries Government Documents Department
A method for determining the column curve from tests of columns with equal restraints against rotation on the ends

A method for determining the column curve from tests of columns with equal restraints against rotation on the ends

Date: August 1, 1943
Creator: Lundquist, Eugene E; Rossman, Carl A & Houbolt, John C
Description: The results are presented of a theoretical study for the determination of the column curve from tests of column specimens having ends equally restrained against rotation. The theory of this problem is studied and a curve is shown relating the fixity coefficient c to the critical load, the length of the column, and the magnitude of the elastic restraint. A method of using this curve for the determination of the column curve for columns with pin ends from tests of columns with elastically restrained ends is presented. The results of the method as applied to a series of tests on thin-strip columns of stainless steel are also given.
Contributing Partner: UNT Libraries Government Documents Department
Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds

Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds

Date: February 1, 1943
Creator: Delano, James B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Stability of Isotropic or Orthotopic Cylinders or Flat or Curved Panels, Between and Across Stiffeners, with Any Edge Conditions Between Hinged and Fixed, Under Any Combination of Compression and Shear

The Stability of Isotropic or Orthotopic Cylinders or Flat or Curved Panels, Between and Across Stiffeners, with Any Edge Conditions Between Hinged and Fixed, Under Any Combination of Compression and Shear

Date: December 1, 1943
Creator: Donnell, L H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Torsion of flanged members with cross sections restrained against warping

Torsion of flanged members with cross sections restrained against warping

Date: March 1, 1943
Creator: Hill, H N
Description: The longitudinal stresses and the stiffness of flange members - I-beams, channels, and Z-bars - were investigated when these members were subjected to torque with constraint against cross-sectional warping. Measured angles of rotation agreed with corresponding calculated values in which the torsion bending factor of the cross section was involved; the agreement was better for the I-beam and the Z-bar than for the channel. Longitudinal stresses measured at the mid-span were found to agree with the calculated values that involved unit warping as well as the torsion-bending factors: the channel showed the greatest discrepancy between measured and calculated values. When commonly given expressions for rotations and maximum longitudinal stresses in a twisted I-beam were applied to the channel and to the Z-bar, values were obtained that were in reasonably good agreement with values obtained by the method of torsion-bending constant and unit warping.
Contributing Partner: UNT Libraries Government Documents Department
Round heat-treated chromium-molybdenum-steel tubing under combined loads

Round heat-treated chromium-molybdenum-steel tubing under combined loads

Date: July 1, 1943
Creator: Osgood, William R
Description: The results of tests of round heat-treated chromium-molybdenum-steel tubing are presented. Tests were made on tubing under axial load, bending load, torsional load, combined bending and axial load, combined bending and torsional load, and combined axial, bending, and torsional load. Tensile and compressive tests were made to determine the properties of the material. Formulas are given for the evaluation of the maximum strength of this steel tubing under individual or combined loads. The solution of an example is included to show the procedure to be followed in designing a tubular cantilever member to carry combined loads.
Contributing Partner: UNT Libraries Government Documents Department
Some investigations of the general instability of stiffened metal cylinders VII : stiffened metal cylinders subjected to combined bending and torsion

Some investigations of the general instability of stiffened metal cylinders VII : stiffened metal cylinders subjected to combined bending and torsion

Date: November 1, 1943
Creator: unknown
Description: This report summarizes the work that has been carried on in the experimental investigation of the problem of the general instability of stiffened metal cylinders subjected to combined bending and torsion at the C.I.T. This part of the investigation included tests on 26 sheet-covered specimens. An interaction curve for the case of combined bending and torsion is presented. The results of tests of 17 specimens subjected to pure torsion are also given.
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
Large-deflection theory for end compression of long rectangular plates rigidly clamped along two edges

Large-deflection theory for end compression of long rectangular plates rigidly clamped along two edges

Date: January 1, 1943
Creator: Levy, Samuel & Krupen, Philip
Description: The von Karman equations for flat plates are solved beyond the buckling load up to edge strains equal to eight time the buckling strain, for the extreme case of rigid clamping along the edges parallel to the load. Deflections, bending stresses, and membrane stresses are given as a function of end compressive load. The theoretical values of effective width are compared with the values derived for simple support along the edges parallel to the load. The increases in effective width due to rigid clamping drops from about 20 percent near the buckling strain to about 8 percent at an edge strain equal to eight times the buckling strain. Experimental values of effective width in the elastic range reported in NACA Technical Note No. 684 are between the theoretical curves for the extremes of simple support and rigid clamping.
Contributing Partner: UNT Libraries Government Documents Department
Torsional strength of aluminum-alloy round tubing

Torsional strength of aluminum-alloy round tubing

Date: January 1, 1943
Creator: Moore, R L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tensile and compressive tests of magnesium alloy J-1 sheet

Tensile and compressive tests of magnesium alloy J-1 sheet

Date: December 1, 1943
Creator: Aitchison, C S & Miller, James A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of flat panels with four types of stiffeners

Tests of flat panels with four types of stiffeners

Date: January 1, 1943
Creator: Niles, Alfred S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bearing strengths of some wrought-aluminum alloys

Bearing strengths of some wrought-aluminum alloys

Date: August 1, 1943
Creator: Moore, R L & Wescoat, C
Description: Although a number of investigations of the bearing strength of aluminum alloys have been made, the problem remains one of considerable interest to the aircraft industry. For this reason it has seemed advisable to make additional tests of the commonly used aircraft alloys in an effort to establish a better basis for the selection of allowable bearing values. Current design practice does not recognize the effect of edge distance upon bearing strengths, and for this reason edge distance was one of the principal variables considered in this investigation. The increasing emphasis being placed upon permanent set limitations makes it essential that more information on bearing yield phenomena be obtained. The object of this investigation was to determine bearing yield and ultimate strengths of the following aluminum alloy products: 17S-T, 24S-T, Alclad 24S-T, 24S-RT, 52S-0, 52S-1/2H, 52S-H, 53S-T, and 61S-T extrusions. Ratios of these bearing properties to tensile properties were also determined.
Contributing Partner: UNT Libraries Government Documents Department
Bearing tests of magnesium-alloy sheet

Bearing tests of magnesium-alloy sheet

Date: June 1, 1943
Creator: Sharp, W H & Moore, R L
Description: Bearing tests of AM-3S, AM-52S, and AM-C57S magnesium-alloy sheet in various thicknesses and tempers were made. Bearing yield and ultimate strengths were determined and compared for various edge distances and for various ratios of loading-pin diameter to sheet thickness. Tensile strengths were determined and ratios of average bearing yield and ultimate strength to tensile strength are given. The results of the tests indicated that ultimate bearing strengths increased with edge distances up to 1.5 to 2 times the diameter of the loading pin; that ultimate bearing strengths are a function of the ratio of pin diameter to sheet thickness; and that these properties are effected only slightly by increases in edge distance greater than 1.5 diameters.
Contributing Partner: UNT Libraries Government Documents Department
The effect of surface finish on the fatigue performance of certain propeller materials

The effect of surface finish on the fatigue performance of certain propeller materials

Date: December 1, 1943
Creator: Russell, H W; Gillett, H W; Jackson, L R & Foley, G M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Torsion tests of 24S-T aluminum-alloy noncircular bar and tubing

Torsion tests of 24S-T aluminum-alloy noncircular bar and tubing

Date: January 1, 1943
Creator: Moore, R L & Paul, D A
Description: Tests of 24S-T aluminum alloy have been made to determine the yield and ultimate strengths in torsion of noncircular bar and tubing. An approximate basis for predicting these torsional strength characteristics has been indicated. The results show that the torsional stiffness and maximum shearing stresses within the elastic range may be computed quite closely by means of existing formulas based on mathematical analysis and the membrane analogy.
Contributing Partner: UNT Libraries Government Documents Department
Effects of prior fatigue-stressing of the impact resistance of chromium-molybdenum aircraft steel

Effects of prior fatigue-stressing of the impact resistance of chromium-molybdenum aircraft steel

Date: March 1, 1943
Creator: Kies, J A & Holshouser, W L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of rivet pitch upon the fatigue strength of single-row riveted joints of 0.025- to 0.025-inch 24S-T alclad

Effect of rivet pitch upon the fatigue strength of single-row riveted joints of 0.025- to 0.025-inch 24S-T alclad

Date: July 1, 1943
Creator: Seliger, Victor
Description: S-N curves at the range ratio of 0.2 were experimentally obtained for each of the following values of rivet pitch P as used in a single-row lap joint of 0.025- to 0.025-inch 24S-T alclad with one-eight AN430 round-head rivets: p=0.5, 0.75, 1.0, 1.5. Families of constant rivet pitch curves, which define the fatigue life for specimens studied, were developed. Curves showing the variation of the effective stress concentration factor in fatigue with rivet pitch and maximum load per rivet were also established.
Contributing Partner: UNT Libraries Government Documents Department
Certain mechanical strength properties of aluminum alloys 25S-T and X76S-T

Certain mechanical strength properties of aluminum alloys 25S-T and X76S-T

Date: October 1, 1943
Creator: Dolan, Thomas J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of the type of specimen on the shear strengths of driven rivets

The effect of the type of specimen on the shear strengths of driven rivets

Date: November 1, 1943
Creator: Sharp, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of aluminum-alloy stiffened-sheet specimens cut from an airplane wing

Tests of aluminum-alloy stiffened-sheet specimens cut from an airplane wing

Date: January 1, 1943
Creator: Holt, Marshall
Description: The specimens used in the present tests were cut from an actual airplane wing of the stressed-skin type. The specimens thus obtained were not representative of the usual type of laboratory specimens because the stiffeners were not exactly parallel nor evenly spaced and, in one case, the skin consisted of pieces of sheet of different thicknesses. The test data obtained indicate that the buckling strain of stiffened curved sheet can be computed with reasonable accuracy by the equation given by Wenzek. The ultimate loads of the specimens when tested as flat sheet were within +/-11 percent of the product of the compressive yield strength and the cross-sectional area of the stiffeners. A rivet spacing equal to 98 times the sheet thickness was a source of weakness, and rivet spacings up to 36 times the sheet thickness appeared satisfactory.
Contributing Partner: UNT Libraries Government Documents Department
A portable calibrator for dynamic strain gages

A portable calibrator for dynamic strain gages

Date: February 1, 1943
Creator: Mcpherson, Albert E
Description: A portable device for calibrating dynamic strain gages is described. The device contains a motor-driven cam, which applies alternating tensile loads to a metal strip 5/8 inch wide and 6 1/4 inches long. The cam is designed to produce a nearly sinusoidal variation of strain with time. Dynamic strain gages with gage lengths up to 5 inches may be calibrated by mounting them on the strip and by changing the frequency and the amplitude of the tensile load. The frequency may be varied from 15 to 30 cycles per second and the strain amplitude from 0 to 10x10-4 in steps of 2x10-4.
Contributing Partner: UNT Libraries Government Documents Department
Description of stress-strain curves by three parameters

Description of stress-strain curves by three parameters

Date: July 1, 1943
Creator: Ramberg, Walter & Osgood, William R
Description: A simple formula is suggested for describing the stress-strain curve in terms of three parameters; namely, Young's modulus and two secant yield strengths. Dimensionless charts are derived from this formula for determining the stress-strain curve, the tangent modulus, and the reduced modulus of a material for which these three parameters are given. Comparison with the tensile and compressive data on aluminum-alloy, stainless-steel, and carbon-steel sheet in NACA Technical Note No. 840 indicates that the formula is adequate for most of these materials. The formula does not describe the behavior of alclad sheet, which shows a marked change in slope at low stress. It seems probable that more than three parameters will be necessary to represent such stress-strain curves adequately.
Contributing Partner: UNT Libraries Government Documents Department
Turbulent flow between rotating cylinders

Turbulent flow between rotating cylinders

Date: March 1, 1943
Creator: Shih-I, Pai
Description: The turbulent air flow between rotating cylinders was investigated. The distributions of mean speed and of turbulence were measured in the gap between a rotating inner and a stationary outer cylinder. The measurements led to the conclusion that the turbulent flow in the gap cannot be considered two dimensional, but that a particular type of secondary motion takes place. It is shown that the experimentally found velocity distribution can be fully understood under the assumption that this secondary motion consists of three-dimensional ring-shape vortices. The vortices occur only in pairs, and their number and size depend on the speed of the rotating cylinder; the number was found to decrease with increasing speed. The secondary motion has an essential part in the transmission of the moment of momentum. In regions where the secondary motion is negligible, the momentum transfer follows the laws known for homologous turbulence. Ring-shape vortices are known to occur in the laminar flow between rotating cylinders, but it was hitherto unknown that they exist even at speeds that are several hundred times the critical limit.
Contributing Partner: UNT Libraries Government Documents Department
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