Published January 1955
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A simple laminar boundary layer with secondary flow
- Creators
- Loos, Henk G.
Chicago
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Abstract
The incompressible laminar boundary layer over a flat plate is studied for the simple case where the stream lines in the free flow have a parabolic shape. An exact solution of the boundary layer equations is derived. No separation occurs, even when there is a strong adverse pressure gradient along the stream lines, so that in this instance the secondary flow has a favorable influence. Because of the variation of total pressure from one stream line to another in the free stream, the total pressure within the boundary layer at a given point can exceed that of the corresponding free stream.
Additional Information
© 1954 Institute of the Aeronautical Sciences. Received February 22, 1954. This work was carried out under the sponsorship of the Office of Scientific Research, Air Research and Development Command and represents a portion of an investigation into secondary flow in axial compressors. The author wishes to express his appreciation to Drs. H. S. Tsien and F. E. Marble for many stimulating discussions.Attached Files
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Additional details
- Eprint ID
- 21792
- Resolver ID
- CaltechAUTHORS:20110118-132624864
- Created
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2011-01-28Created from EPrint's datestamp field
- Updated
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2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center
- Other Numbering System Name
- Guggenheim Jet Propulsion Center