A Caltech Library Service

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


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.


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)
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1955
Record Number:CaltechETD:etd-11242003-104401
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:4648
Deposited By: Imported from ETD-db
Deposited On:24 Nov 2003
Last Modified:28 Jun 2023 17:40

Thesis Files

PDF (Baldwin_lc_1955.pdf) - Final Version
See Usage Policy.


Repository Staff Only: item control page