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Oscillating supersonic delta wings with straight leading edges

Crasta, Asha and Khan, Sher Afghan (2012) Oscillating supersonic delta wings with straight leading edges. International Journal of Computational Engineering Research,, 2 (5). pp. 12028-12035. ISSN 2250-3005

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Abstract

A Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with straight leading edge for the attached shock case. Ghosh’s strip theory is been used in which strips at different span wise locations are independent of each other. This combines with the similitude to give a piston theory which gives the closed form of solution to stability derivatives in pitch and roll. Some of the results obtained have been compared with those of Hui et al ,Ghosh and Lui &Hui. Results have been obtained for supersonic flow of perfect gas over a wide range of Mach numbers, incidences and sweep angles

Item Type: Article (Journal)
Additional Information: 7395/49943
Uncontrolled Keywords: Aspect ratio, Attached shock wave, Delta wings, Damping derivative, Leading edge, Rolling derivative, Stiffness derivative, Supersonic Flow, unsteady flow
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics
T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL787 Astronautics
Kulliyyahs/Centres/Divisions/Institutes: Kulliyyah of Engineering > Department of Mechanical Engineering
Depositing User: Prof. Dr. Sher Afghan Khan
Date Deposited: 20 Apr 2016 03:09
Last Modified: 20 Apr 2016 03:09
URI: http://irep.iium.edu.my/id/eprint/49943

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