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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Collection: National Advisory Committee for Aeronautics Collection
Tension fields in originally curved, thin sheets during shearing stresses

Tension fields in originally curved, thin sheets during shearing stresses

Date: August 1, 1935
Creator: Wagner, H
Description: The analysis of the stresses in the sheet and stiffeners is predicated upon the direction of the wrinkles, particularly the tensile stresses (principal stresses). This analysis and the calculation of stresses after buckling form the subject of the present article. It includes: 1) metal cylinders with closely spaced longitudinal stiffeners; 2) metal cylinders with closely spaced transverse rings.
Contributing Partner: UNT Libraries Government Documents Department
Test of an adjustable pitch model propeller at four blade settings

Test of an adjustable pitch model propeller at four blade settings

Date: February 1, 1930
Creator: Lesley, E P
Description: This note describes tests of an adjustable blade metal model propeller, both in a free wind stream and in combination with a model fuselage, at four settings of the blades. The model propeller is designed for a uniform nominal pitch/diameter ratio of .7 and the blade settings used correspond to nominal pitch/diameter ratios of .5, .7, .9, and 1.1 at the .6 radius. The tests show that propellers of this type may be considerably changed in setting from the designed pitch angles and yet give excellent performance. The efficiency realized and power absorbed when blades are set at other than the designed angle, are little different than would be obtained from a propeller with uniform pitch equal to the mean pitch of the propeller under test.
Contributing Partner: UNT Libraries Government Documents Department
The testing of airplane fabrics

The testing of airplane fabrics

Date: November 1, 1932
Creator: Schraivogel, Karl
Description: This report considers the determining factors in the choice of airplane fabrics, describes the customary methods of testing and reports some of the experimental results. To sum up briefly the results obtained with the different fabrics, it may be said that increasing the strength of covering fabrics by using coarser yarns ordinarily offers no difficulty, because the weight increment from doping is relatively smaller.
Contributing Partner: UNT Libraries Government Documents Department
Tests for the determination of the stress condition in tension fields

Tests for the determination of the stress condition in tension fields

Date: November 1, 1936
Creator: Lahde, R
Description: The present experiments treat the stress of actual tension fields within the elastic range. They give the magnitude of the flexural stresses due to wrinkling. They also disclose, particularly by slightly exceeded buckling load, the marked unloading - as compared with the tension-field theory - of the uprights as a result of the flexural stiffness of the web plate. The test sheets were clamped at the edges and brought to buckling through shearing and compressive stresses applied in the direction of the long sides.
Contributing Partner: UNT Libraries Government Documents Department
Tests for the elimination of tail flutter

Tests for the elimination of tail flutter

Date: June 1, 1933
Creator: Biechteler, Curt
Description: On various low-wing monoplanes the horizontal tail surfaces flutter in flight at large angles of attack and occasionally in curvilinear flight. This flutter leads to torsional vibrations of the rear end of the fuselage, as manifested by vibrations of the control stick. According to the earlier DVL investigations tail flutter is due to the influence, on horizontal tail surfaces, of eddies or vortices shed at large angles of attack by the upper surface of the wing root. The cause of tail flutter on a low-wing monoplane and the means of preventing it are investigated in the present report.
Contributing Partner: UNT Libraries Government Documents Department
Tests in the gust tunnel of a model of the XBM-1 airplane

Tests in the gust tunnel of a model of the XBM-1 airplane

Date: October 1, 1939
Creator: Donely, Philip
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report

Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report

Date: August 1, 1937
Creator: Anderson, Raymond F.
Description: At the request of the Materiel Division of the Army Air Corps, seven tapered wings having sections based on the N.A,C.A. 230 mean line were tested in the variable-density wind tunnel, The characteristics of the wings are given.
Contributing Partner: UNT Libraries Government Documents Department
Tests in the variable-density wind tunnel of related airfoils having the maximum camber unusually far forward

Tests in the variable-density wind tunnel of related airfoils having the maximum camber unusually far forward

Date: January 1, 1936
Creator: Jacobs, Eastman N
Description: A family of related airfoils having the position of maximum camber unusually far forward was investigated in the variable-density tunnel as an extension of the study recently completed of a large number of related airfoils. The new airfoils gave improved characteristics over those previously investigated, especially in regard to the pitching moment. Some of the new sections are markedly superior to well-known and commonly used sections and should replace them in applications requiring a slightly cambered section of moderate thickness having a small pitching-moment coefficient.
Contributing Partner: UNT Libraries Government Documents Department
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps

Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps

Date: January 1, 1939
Creator: Abbott, Ira H
Description: Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics

Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics

Date: February 1, 1931
Creator: Stack, John
Description: The effect of scale and turbulence on the lift and drag of five airfoils the NACA 0006, the NACA 0021, the Clark Y and the USA 35-A, and the USN PS6, have been investigated in the Variable Density Wind Tunnel of the NACA. Tests were made over a wide scale range for only two different conditions of turbulence.
Contributing Partner: UNT Libraries Government Documents Department