Published December 1946
| public
Journal Article
The Interaction Between Boundary Layer and Shock Waves in Transonic Flow
- Creators
- Liepmann, Hans Wolfgang
Chicago
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Abstract
Experiments of transonic flow past a circular arc profile show that the shock-wave pattern and the pressure distribution are strongly dependent upon the state of the boundary layer. A change from laminar to turbulent boundary layer at a given Mach Number changes the flow pattern considerably. Shock waves can interact with the boundary layer in a manner similar to a reflection from a free jet boundary. These shock waves are not distinctly discernible from pressure distribution measurements.
Additional Information
The author wishes to acknowledge the cooperation of Mrs. K. Liepmann and of Messrs. H. Ashkenas and J. D. Cole.Additional details
- Alternative title
- Investigations of the Interaction of Boundary Layer and Shock Waves in Transonic Flow
- Eprint ID
- 119910
- Resolver ID
- CaltechAUTHORS:20230309-962584000.1
- Created
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2023-03-13Created from EPrint's datestamp field
- Updated
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2023-03-13Created from EPrint's last_modified field
- Caltech groups
- GALCIT