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...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | en |
| Published: |
AerosocietyofIndia
1990
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/49889/1/K-ghosh.pdf http://irep.iium.edu.my/49889/ http://www.aerosocietyindia.in |
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