Supersonic laminar boundary layer separation near a compression corner
Detailed measurements were performed in the region of interaction of a laminar boundary layer with a compression corner at Mach numbers near 2.5. Different models were tested permitting variation in the angle of compression and the conditions downstream of reattachment. The heat flux and the resista...
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| Format: | masterThesis |
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1969
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| Online Access: | http://hdl.handle.net/10725/6443 http://libraries.lau.edu.lb/research/laur/terms-of-use/articles.php http://www.dtic.mil/dtic/tr/fulltext/u2/687483.pdf |
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