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Effect of spin and yaw on boundary layer transition along a body of revolution

Citation

Fehrman, Alvin L (1955) Effect of spin and yaw on boundary layer transition along a body of revolution. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-12092003-160300

Abstract

This report covers an experimental investigation of boundary layer transition on a body of revolution at low subsonic speeds, with emphasis placed on the effects of spin and yaw on transition.

The methods tried for detecting boundary layer transition for this particular investigation are reviewed and the technique finally adopted, the use of a hot wire anemometer, is described in detail.

It was found that at angles of yaw, the transition from laminar to turbulent flow in the boundary layer occurs at a higher Reynolds number over most of the body than at zero yaw, and that spin has a negligible effect on the transition Reynolds number. It was observed however that the effect of spin varies from the front to the rear of the body, although it was not ascertained whether this effect was a result of the influence of the nose section, the tripping device which was used to obtain transition, or a combination of both.

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):
  • Roshko, Anatol (advisor)
  • Millikan, Clark Blanchard (advisor)
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1955
Record Number:CaltechETD:etd-12092003-160300
Persistent URL:http://resolver.caltech.edu/CaltechETD:etd-12092003-160300
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:4891
Collection:CaltechTHESIS
Deposited By: Imported from ETD-db
Deposited On:12 Dec 2003
Last Modified:26 Dec 2012 03:12

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