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) |
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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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