Estimation of surface pressure distribution on a delta wing with curved leading edges in hypersonic/supersonic flow

Crasta, Asha and Pavithra, S and Khan, Sher Afghan (2016) Estimation of surface pressure distribution on a delta wing with curved leading edges in hypersonic/supersonic flow. International Journal of Energy, Environment, and Economics, 24 (1). pp. 67-73. ISSN 1054-853X

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Abstract

In this paper the focus is on study of surface pressure distribution variation with angle of incidence and Mach number for hypersonic flow/Supersonic flow for a delta wing with leading edges which are curved. It is found that the surface pressure on the wing increases with increase in incidence angle and the inertia level. Results are compared for M = 8.7, 10, and 17 for delta wing with leading edge straight and curved and the results are found to be in good agreement with existing theories.

Item Type:	Article (Journal)
Additional Information:	7395/53341
Uncontrolled Keywords:	angle of incidence, hypersonic, supersonic, surface pressure distribution
Subjects:	T Technology > T Technology (General) > T175 Industrial research. Research and development
Kulliyyahs/Centres/Divisions/Institutes (Can select more than one option. Press CONTROL button):	Kulliyyah of Engineering > Department of Mechanical Engineering
Depositing User:	Prof. Dr. Sher Afghan Khan
Date Deposited:	12 Dec 2016 17:43
Last Modified:	15 Mar 2017 10:15
URI:	http://irep.iium.edu.my/id/eprint/53341

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