Effect of angle of attack on damping derivatives of delta wing with full sine wave curved leading edge
In the Present paper effect of angle of incidence on Damping derivative of a delta wing with Curved leading edges (for a full sine wave) for attached shock case in Supersonic Flow has been studied. A Strip theory is used in which strips at different span wise location are independent of each other....
Saved in:
| Main Authors: | , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
RS Publication
2015
|
| Subjects: | |
| Online Access: | http://irep.iium.edu.my/49928/1/paper21.pdf http://irep.iium.edu.my/49928/ http://rspublication.com/ijeted/ijeted_archive.htm |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|