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

Ghosh, K and Murthy, M and Khan, Sher Afghan and Pandey, P K (1990) Pitch and roll derivatives of a delta wing with curved leading edge in high speed flow. Aeronautical Society of India, 42 (4). pp. 299-302. ISSN 0972-950X

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Abstract

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 moment derivative due to the incidence rate is obtained by combining Ghosh's unsteady theory and the quasi-steady theory. The results are compared with Hui et. al. The shock is assumed to be attached to the leading edge. The effects of viscosity and real gas have not been included.

Item Type: Article (Journal)
Additional Information: 7395/49889
Uncontrolled Keywords: Ghosh, Delta wing, Hypersonic, Supersonic/hyper- sonic flow
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500 Aeronautics
Kulliyyahs/Centres/Divisions/Institutes: Kulliyyah of Engineering > Department of Mechanical Engineering
Depositing User: Prof. Dr. Sher Afghan Khan
Date Deposited: 13 Apr 2016 10:46
Last Modified: 13 Apr 2016 10:46
URI: http://irep.iium.edu.my/id/eprint/49889

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