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

Citation

Baldwin, Lawrence Cloyd (1955) Viscous Effects on Static Pressure Distribution for a Slender Cone at a Nominal Mach Number of 5.8. Engineer's thesis, California Institute of Technology. doi:10.7907/XNB2-P865. https://resolver.caltech.edu/CaltechETD:etd-11242003-104401

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.

Item Type:	Thesis (Engineer's thesis)
Subject Keywords:	Aeronautical Engineering
Degree Grantor:	California Institute of Technology
Division:	Engineering and Applied Science
Major Option:	Aeronautics
Thesis Availability:	Public (worldwide access)
Research Advisor(s):	Lees, Lester (advisor) Nagamatsu, Henry T. (advisor)
Group:	GALCIT
Thesis Committee:	Unknown, Unknown
Defense Date:	1 January 1955
Record Number:	CaltechETD:etd-11242003-104401
Persistent URL:	https://resolver.caltech.edu/CaltechETD:etd-11242003-104401
DOI:	10.7907/XNB2-P865
Default Usage Policy:	No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:	4648
Collection:	CaltechTHESIS
Deposited By:	Imported from ETD-db
Deposited On:	24 Nov 2003
Last Modified:	28 Jun 2023 17:40

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