Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow
Ghosh's unified similitude has been applied to oscillating delta wings of arbitrary plan forms in supersonic/ hyper- sonic flow. The quasi-steady derivative which was obtained by Ghosh for a hypersonic delta wing is extended to supersonic Mach number and curved leading edges. The unsteady momen...
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
AerosocietyofIndia
1990
|
| Subjects: | |
| Online Access: | http://irep.iium.edu.my/49889/ http://irep.iium.edu.my/49889/ http://irep.iium.edu.my/49889/1/K-ghosh.pdf |