Viscous Effects on Static Pressure Distribution for a Slender Cone at a Nominal Mach Number of 5.8

Author: Baldwin, Lawrence Cloyd

Year: 1955

Degree: Engineer's thesis

Advisors: Lees, Lester; Nagamatsu, Henry T.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/XNB2-P865

Abstract

An experimental investigation was conducted in the GALCIT Hypersonic Wind Tunnel, Leg No. 1, to determine the static pressure distribution on a cone with 5[degrees] semivertex angle at a nominal Mach number of 5.8.

This investigation was concerned with the effect of hypersonic boundary layer-shock wave interaction on the pressure at the cone surface. Pressure distributions were measured for three values of Reynolds numbers per inch and a comparison was made with theoretically calculated pressure distributions.

The influence of viscosity in hypersonic flow was demonstrated by an induced pressure rise of approximately 45% above theoretical inviscid pressure for the lowest Reynolds number tested.

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