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...
محفوظ في:
| المؤلف الرئيسي: | |
|---|---|
| التنسيق: | masterThesis |
| منشور في: |
1969
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| الموضوعات: | |
| الوصول للمادة أونلاين: | 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 |
| الوسوم: |
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