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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Test data on the shear strength of machine countersunk-riveted joints assembled by an NACA flush-riveting procedure

Test data on the shear strength of machine countersunk-riveted joints assembled by an NACA flush-riveting procedure

Date: December 1, 1942
Creator: Gottlieb, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test flight of the Handley Page torpedo-carrying airplane

Test flight of the Handley Page torpedo-carrying airplane

Date: April 1, 1922
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test Manual (Tentative) For Permselective Membranes

Test Manual (Tentative) For Permselective Membranes

Date: January 1964
Creator: United Stats. Bureau of Reclamation.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of 0.14-scale models of the control surfaces of Army project MX-511 in attitudes simulating spins

Test of 0.14-scale models of the control surfaces of Army project MX-511 in attitudes simulating spins

Date: April 1, 1945
Creator: Hagerman, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of a dual-rotation axial-flow fan

Test of a dual-rotation axial-flow fan

Date: December 1, 1942
Creator: Dekoster, Lucas J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of a model propeller with symmetrical blade sections

Test of a model propeller with symmetrical blade sections

Date: September 1, 1926
Creator: LESLEY E P
Description: This report, prepared at the request of NACA, gives the results of tests on a model propeller having blade sections with form of Gottingen airfoil no. 409. The model is shown to have a dynamic pitch practically equal to the nominal or geometrical pitch, and a somewhat higher efficiency but lower coefficient than would be expected of a propeller of more conventional sections.
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
Test of an aerodynamically heated multiweb wing structure (MW-1) in a free jet at Mach number 2

Test of an aerodynamically heated multiweb wing structure (MW-1) in a free jet at Mach number 2

Date: July 30, 1953
Creator: Heldenfels, Richard R; Rosecrans, Richard & Griffith, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Date: May 1, 1942
Creator: Abbott, Frank T , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of single-stage axial-flow fan

Test of single-stage axial-flow fan

Date: January 1, 1942
Creator: Bell, E Barton
Description: A single-stage axial fan was built and tested in the shop of the propeller-research tunnel of the NACA. The fan comprised a simple 24-blade rotor having a diameter of 21 inches and a solidity of 0.86 and a set of 37 contravanes having a solidity of 1.33. The rotor was driven by a 25-horsepower motor capable of rotating at a speed of 3600 r.p.m. The fan was tested for volume, pressure, and efficiency over a range of delivery pressures and volumes for a wide range of contravane and blade-angle settings. The test results are presented in chart form in terms of nondimensional units in order that similar fans may be accurately designed with a minimum effort. The maximum efficiency (88 percent) was obtained by the fan at a blade angle of 30 degrees and a contravane angle of 70 degrees. An efficiency of 80 percent was obtained by the fan with the contravanes removed.
Contributing Partner: UNT Libraries Government Documents Department