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Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow

Crasta, Asha and Khan, Sher Afghan (2016) Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow. International Journal of Advances in Engineering Research (IJAER), 12 (1). pp. 10-15. ISSN 2454-1796 E-ISSN 2231-5152

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In this paper attention is focussed on study of effect of Aspect ratio of the wing on roll moment derivatives at various angle of attack and Mach number for a Supersonic flow. It is been observed that there is a linear increment in rolling moment derivative with aspect ratio as well as with Angle of attack. The reason behind this being rolling moment derivative is a linear function of aspect ratio and angle of attack. The requirement for the validity of the present theory is the attachment of the shock at the leading edge of the wing. Whereas, in the case of detached shock wave, this theory is not valid.

Item Type: Article (Journal)
Additional Information: 7395/50991
Uncontrolled Keywords: Aspect ratio, inertia, rolling moment derivative, supersonic, wing
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500 Aeronautics
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: 28 Jun 2016 11:51
Last Modified: 27 Jul 2016 17:26
URI: http://irep.iium.edu.my/id/eprint/50991

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