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. 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) |
|---|---|
| Degree Grantor: | California Institute of Technology |
| Division: | Engineering and Applied Science |
| Major Option: | Aeronautics |
| Thesis Availability: | Public (worldwide access) |
| Research Advisor(s): |
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| Group: | GALCIT |
| Thesis Committee: |
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| 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: | 21 Dec 2019 02:18 |
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