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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Tests of six symmetrical airfoils in the variable density wind tunnel

Tests of six symmetrical airfoils in the variable density wind tunnel

Date: July 1, 1931
Creator: Jacobs, Eastman N
Description: This paper is the first of a series covering an investigation of a family of airfoils all formed from a basic profile. It gives in preliminary form the results of six symmetrical airfoils, differing only in maximum thickness. The maximum thickness-to-chord ratios are 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21.
Contributing Partner: UNT Libraries Government Documents Department
Tests of spheres with reference to Reynolds number, turbulence, and surface roughness

Tests of spheres with reference to Reynolds number, turbulence, and surface roughness

Date: October 1, 1935
Creator: Hoerner, S
Description: The behavior of the Reynolds Number of the sphere is explained (in known manner) with the aid of the boundary-layer theory. Rear spindles may falsify, under certain conditions, the supercritical sphere drag, while suspension wires in the space behind the sphere leave no traceable influence. The critical Reynolds Number of the sphere was arrived at by an unconventional method; that is, by determining the critical wind speed at which the static pressure at the back of the sphere is the same as that of the undisturbed flow. The method makes it possible to interpret the critical Reynolds Number with only one test station.
Contributing Partner: UNT Libraries Government Documents Department
Tests of Strength of Roof Supports Used in Anthracite Mines of Pennsylvania

Tests of Strength of Roof Supports Used in Anthracite Mines of Pennsylvania

Date: 1929
Creator: United States. Bureau of Mines.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of submerged duct installation on a modified airplane in the Ames 40- by 80-foot wind tunnel

Tests of submerged duct installation on a modified airplane in the Ames 40- by 80-foot wind tunnel

Date: December 11, 1947
Creator: Martin, Norman J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of Submerged Duct Installation on the Ryan FR-1 Airplane in the Ames 40- by 80-Foot Wind Tunnel

Tests of Submerged Duct Installation on the Ryan FR-1 Airplane in the Ames 40- by 80-Foot Wind Tunnel

Date: April 23, 1947
Creator: Martin, Norman J.
Description: An investigation of an NACA submerged intake installation on the Ryan FR-1 was conducted to determine the full-scale aerodynamic characteristics of this installation. In addition, tests were conducted on the submerged inlet with revised entrance lips and deflectors to determine the configuration which would result in the best dynamic pressure recovery measured at the inlet for this installation without a major rework of the entrance. Stalling of the air flow over the inner lip surface created excessive dynamic pressure losses with the original entrance. The revised entrance produced a 12-percent increase in dynamic pressure recovery at the design high-speed inlet-velocity ratio and resulted in an improvement of thte critical-speed characteristics of the entrance lip. A complete redesign of the entrance including a decrease in ramp angle and adjustment of lip camber is necessary to secure optimum results from this submerged duct installation.
Contributing Partner: UNT Libraries Government Documents Department
Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Date: December 22, 1947
Creator: May, Ralph W., Jr.
Description: Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectively.
Contributing Partner: UNT Libraries Government Documents Department
Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Date: January 1, 1948
Creator: May, Ralph W., Jr.
Description: Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245 deg. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectively.
Contributing Partner: UNT Libraries Government Documents Department
Tests of the Anthratube

Tests of the Anthratube

Date: January 1953
Creator: Barkley, J. F.; Burdick, L. R. & Morgan, R. E.
Description: Report issued by the U.S. Bureau of Mines on the equipment testing of the Anthratube. The report follows the methods used and the results gained from testing the Anthratube. This report includes tables of data, as well as illustrations and photographs of equipment tested.
Contributing Partner: UNT Libraries Government Documents Department
Tests of the Daimler D-IVa engine at a high altitude test bench

Tests of the Daimler D-IVa engine at a high altitude test bench

Date: October 1, 1920
Creator: Noack, W G
Description: Reports of tests of a Daimler IVa engine at the test-bench at Friedrichshafen, show that the decrease of power of that engine, at high altitudes, was established, and that the manner of its working when air is supplied at a certain pressure was explained. These tests were preparatory to the installation of compressors in giant aircraft for the purpose of maintaining constant power at high altitudes.
Contributing Partner: UNT Libraries Government Documents Department
Tests of the jet-motor air-intake duct system on a 1/4-scale stub-wing model of a pursuit-type airplane

Tests of the jet-motor air-intake duct system on a 1/4-scale stub-wing model of a pursuit-type airplane

Date: May 13, 1946
Creator: Hanson, Frederick H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department