Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow

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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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Bibliographic Details
Main Authors:	Ghosh, K, Murthy, M, Khan, Sher Afghan, Pandey, P K
Format:	Article
Language:	English
Published:	AerosocietyofIndia 1990
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/49889/ http://irep.iium.edu.my/49889/1/K-ghosh.pdf

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