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Wind Tunnel Study of the Influence of Orifice Geometry and Flow Rates on the Measured Pressure Error of a Static Pressure Probe at Mach 3
Abstract: Tests were conducted in the Jet Propulsion Laboratory's 20-inch Supersonic Wind Tunnel to determine the effect of hole-spacing geometry on the measured pressure error due to "breathing" for a pressure-sensing probe at Mach 3.01.
Date:
November 1960
Creator:
Zumwalt, Glen W.
System:
The UNT Digital Library
Prediction of Shock Response
Abstract: A method is presented of predicting the shock response of a friction-damped vibratory system.
Date:
November 1960
Creator:
Barba, Peter M.
System:
The UNT Digital Library