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Type of Document	Engineer's Thesis
Author	Baldwin, L. C.
URN	etd-11242003-104401
Persistent URL	http://resolver.caltech.edu/CaltechETD:etd-11242003-104401
Title	Viscous effects on static pressure distribution for a slender cone at a nominal mach number of 5.8
Degree	Engineer's Degree
Option	Aeronautics
Advisory Committee	Advisor Name Title H. T. Nagamatsu Committee Member Lester Lees Committee Member
Keywords	None
Date of Defense	1955-01-01
Availability	unrestricted
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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