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
Description:
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.
Partner:
UNT Libraries Government Documents Department