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Free-Spinning Tunnel Tests of a 1/24-Scale Model of the Grumman XTB3F-1 Airplane, TED No. NACA DE304
In accordance with a request of the Bureau of Aeronautics, Navy Department, tests were performed in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 1/24 scale model of the Grumman XTB3F-1 airplane. The airplane is a two-place, midwing torpedo bomber equipped with a tractor propeller and an auxiliary jet engine. The effect of control setting and movement on the erect and inverted spin and recovery characteristics of the model were determined for the normal loading.
Date:
May 9, 1947
Creator:
Berman, Theodore
System:
The UNT Digital Library
An Electric Thrust Meter Suitable for Flight Investigation of Propellers
A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date:
May 9, 1949
Creator:
Perkins, Porter J., Jr. & Millenson, Morton B.
System:
The UNT Digital Library
Experimental investigation of liquid diborane - liquid oxygen propellant combination in 100-pound-thrust rocket engine
Report presenting the specific impulse of liquid diborane and liquid oxygen over a range of mixture ratios in a 100-pound-thrust rocket engine operating at a combustion-chamber pressure of 300 pounds per square inch absolute. A faired curve through the experimental data had approximately the same shape as the theoretical curve.
Date:
May 9, 1949
Creator:
Rowe, William H.; Ordin, Paul M. & Diehl, John M.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of a Wing Swept-Back 63 Degrees and Twisted and Cambered for a Uniform Load at a Lift Coefficient of 0.5
Report discusses the results of testing to determine the low-speed longitudinal stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, an aspect ratio of 3.5, and a large amount of twist and camber. The results are compared to tests of a model of an untwisted and uncambered wing of identical plan form. Measurements of force, pressure-distribution, and comparison of theoretical and experimental span loading are described.
Date:
May 9, 1950
Creator:
Weiberg, James A. & Carel, Hubert C.
System:
The UNT Digital Library
Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen
Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date:
May 9, 1955
Creator:
Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
System:
The UNT Digital Library