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Viscous effects on static pressure distribution for a slender cone at a nominal mach number of 5.8

Citation

Baldwin, L. C. (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. http://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)
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)
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1955
Record Number:CaltechETD:etd-11242003-104401
Persistent URL:http://resolver.caltech.edu/CaltechETD:etd-11242003-104401
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:26 Dec 2012 03:10

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