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...
Saved in:
| Main Author: | |
|---|---|
| Format: | masterThesis |
| Published: |
1969
|
| Subjects: | |
| 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 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
Be the first to leave a comment!