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Riveting in metal airplane construction. Part III : strength of riveted joints in duralumin (continued)

Riveting in metal airplane construction. Part III : strength of riveted joints in duralumin (continued)

Date: December 1, 1930
Creator: Pleines, Wilhelm
Description: This report includes strength of riveted joints in duralumin, descriptions of test procedure and results of tests. Tabulated data includes: curshing strength by failure for various conditions, shearing strength of hole edge zone in direction of tearing, tearing strengths of plates weakened by rivet holes, and enlargement of holes at beginning of break.
Contributing Partner: UNT Libraries Government Documents Department
Riveting in metal airplane construction. Part IV : strength of riveted joints in duralumin (concluded)

Riveting in metal airplane construction. Part IV : strength of riveted joints in duralumin (concluded)

Date: December 1, 1930
Creator: Pleines, Wilhelm
Description: Tests were made to determine the crushing strength of a riveted joint, in order to define the difference in crushing stregth between a strictly bolted joint and a riveted joint. The object was to tabulate the crushing strength by failure on various plate thicknesses for a one-rivet double-shear riveted joint.
Contributing Partner: UNT Libraries Government Documents Department
Accelerated Laboratory Test for Determination of Slacking Characteristics of Coal

Accelerated Laboratory Test for Determination of Slacking Characteristics of Coal

Date: November 1930
Creator: Fieldner, Arno Carl; Selvig, W. A. & Frederic, W. H.
Description: Report issued by the U.S. Bureau of Mines on laboratory testing developed to measure the slacking of coals. Testing methods and results are presented. This report includes tables and graphs.
Contributing Partner: UNT Libraries Government Documents Department
Bending Tests of Metal Monocoque Fuselage Construction

Bending Tests of Metal Monocoque Fuselage Construction

Date: November 1930
Creator: Mossman, Ralph W.
Description: Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Contributing Partner: UNT Libraries Government Documents Department
Effect of the angular position of the section of a ring cowling on the high speed of an XF7C-1 airplane

Effect of the angular position of the section of a ring cowling on the high speed of an XF7C-1 airplane

Date: November 1, 1930
Creator: Gough, Melvin N
Description: The tests herein reported were conducted by the NACA to determine the effect of the angular position of the section of a ring cowling on the speed of an airplane having a radial air-cooled engine.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of the phenomenon of separation in the air flow around simple quadric cylinders

An investigation of the phenomenon of separation in the air flow around simple quadric cylinders

Date: November 1, 1930
Creator: Parsons, John F & Wallen, Jarvis A
Description: The tests, conducted at the Guggenheim Aeronautical Laboratory of Stanford University, to investigate the phenomenon of separation in the air flow past geometric shapes are described in this report.
Contributing Partner: UNT Libraries Government Documents Department
Mathematical treatise on the recovery from a flat spin

Mathematical treatise on the recovery from a flat spin

Date: November 1, 1930
Creator: Fuchs, R
Description: In this mathematical investigation, made in collaboration with Dr. Wilhelm Schmidt, we interpret the temporary change (due to some disturbance) in the quantities which define the position of the airplane while in a flat spin. We further examine the effect of this change, of the means resorted to to produce the disturbance, and thus reveal the expedients available for recovering from a flat spin.
Contributing Partner: UNT Libraries Government Documents Department
Metal covering of airplanes

Metal covering of airplanes

Date: November 1, 1930
Creator: Mathar, J
Description: This paper presents a relative determination of the wrinkling of a plate wall beam with variable number of supports and methods of attachment. The discussion is based entirely on tests with extensometer readings and number of wrinkles, with complete web and with cutout sections. The author notes that the number of corrugations increase with added stress, keeping constant edge spacing.
Contributing Partner: UNT Libraries Government Documents Department
Practical tests with the "auto control slot." Part I : lecture

Practical tests with the "auto control slot." Part I : lecture

Date: November 1, 1930
Creator: Lachmann, G
Description: For some time the D.V.L. has been investigating the question of applicability of Handley Page slotted wings to German airplanes. Comparitive gliding tests were made with open and closed slots on an Albatros L 75 airplane equipped with the Handley Page "auto control slots." This investigation served to determine the effect of the auto control slot on the properties and performances of airplanes at large angles of attack. The most important problems were whether the angle of glide at small angles of attack can be increased by the adoption of the auto control slot and, in particular, as to whether the flight characteristics at large angles of attack are improved thereby and equilibrium in gliding flight is guaranteed even at larger than ordinary angles of attack.
Contributing Partner: UNT Libraries Government Documents Department
Practical tests with the "auto control slot." Part II : discussion

Practical tests with the "auto control slot." Part II : discussion

Date: November 1, 1930
Creator: Lachmann, G
Description: For some time the D.V.L. has been investigating the question of applicability of Handley Page slotted wings to German airplanes. Comparitive gliding tests were made with open and closed slots on an Albatros L 75 airplane equipped with the Handley Page "auto control slots." This investigation served to determine the effect of the auto control slot on the properties and performances of airplanes at large angles of attack. The most important problems were whether the angle of glide at small angles of attack can be increased by the adoption of the auto control slot and, in particular, as to whether the flight characteristics at large angles of attack are improved thereby and equilibrium in gliding flight is guaranteed even at larger than ordinary angles of attack.
Contributing Partner: UNT Libraries Government Documents Department