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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
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
Test of six types of Bakelite-bonded wire strain gages

Test of six types of Bakelite-bonded wire strain gages

Date: July 1, 1948
Creator: Campbell, William R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of specimen of wood of longerons of the S.E.5 airplane after seven years' service

Test of specimen of wood of longerons of the S.E.5 airplane after seven years' service

Date: August 1, 1922
Creator: unknown
Description: A transverse test was made of the wood sample using a 5,000 pound Olsen testing machine, the deflection under load being measured by means of a Wissler dial. The results of the transverse test are given and the stress-strain curve is attached.
Contributing Partner: UNT Libraries Government Documents Department
Test Plan for Reactions Between Spent Fuel and J-13 Well Water Under Unsaturated Conditions

Test Plan for Reactions Between Spent Fuel and J-13 Well Water Under Unsaturated Conditions

Date: January 1993
Creator: Finn, P. A.; Wronkiewicz, David J.; Hoh, J. C.; Emery, J. W.; Hafenrichter, L. D. & Bates, J. K.
Description: Two complentary test plans are presented, one to examine the reaction of spent fuel and J-13 well water under unsaturated conditions and the second to examine the reaction of unirradiated uranium dioxide pellets and J-13 well water under unsaturated conditions. The former test plan examines the importance of the water content, the oxygen content as affected by radiolysis, the fuel burnup, fuel surface area, and temperature. The latter test plant examines the effect of the non-presence of Teflon in the test vessel.
Contributing Partner: UNT Libraries Government Documents Department
Test Report on Measurements on a Series of Tapered Wings of Small Aspect Ratio (Trapezoidal Wing with Fuselage)

Test Report on Measurements on a Series of Tapered Wings of Small Aspect Ratio (Trapezoidal Wing with Fuselage)

Date: July 1, 1947
Creator: Lange & Wacke
Description: This is the second of a series of six reports dealing with three- and six-component measurements on the tapering series at small aspect ratio. The present report concerns the trapezoidal wing with fuselage.
Contributing Partner: UNT Libraries Government Documents Department
Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio

Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio

Date: May 1, 1948
Creator: Lange & Wacke
Description: The investigations of the reports to 4 on wings of small aspect ratio are continued. The present report deals with the results of the three- and six-component measurements and the flow pictures of the triangular wing series with the aspect ratio Lambda = 3 to Lambda = 1.
Contributing Partner: UNT Libraries Government Documents Department
Test Report on Three-and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Elliptic Wing)

Test Report on Three-and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Elliptic Wing)

Date: June 1, 1947
Creator: Lange & Wacke
Description: The report UM No. 1023/1 which presented the results of measurements for a series of trapezoidal wings was the beginning of a series on wings with aspect ratio 1 to 3 and various contours. In report No. 1023/1 the aspect ratio (Lambda = 4/3) remained the same; the tapering was modified. The present report gives the results of the series of elliptic wings. Here the aspect ratio varies from 1 to 2 with the sweepback. The contour is formed by elliptic arcs. The influence of sweepback and contour upon the neutral point is shown.
Contributing Partner: UNT Libraries Government Documents Department