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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

GLEN W. ZUMWALT

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Abstract

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.

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What this paper is about

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.

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Available abstract

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.

Key concepts: Supersonic wind tunnel, Mach number, Wind tunnel, Supersonic speed, Body orifice, Mechanics, Hypersonic wind tunnel, Pressure measurement

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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 — Research Paper | ScholarLens