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Effect of angle of incidence on stability derivatives of a wing

Crasta, Asha and Khan, Sher Afghan (2014) Effect of angle of incidence on stability derivatives of a wing. International Journal for Research in Applied Science and Engineering Technology (IJRASET), 2 (V). pp. 411-422. ISSN 2321-9653

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Abstract

In the Present paper effect of angle of incidence on pitching derivatives of a delta wing with curved leading edges of a attached shock case is been studied. A Strip theory is used in which strips at different span wise location are independent. This combines with similitude to give a piston theory. From the results it is found that stiffness and damping derivatives in pitch increasing linearly up to angle of attack 250 and then non-linearity creeps in. The Present theory is valid only for attached shock case. Effects of wave reflection and viscosity have not been taken into account. Results have been obtained for hypersonic flow of perfect gases over a wide range of angle of attack and Mach number.

Item Type: Article (Journal)
Additional Information: 7395/49938
Uncontrolled Keywords: Angle of incidence, Attached shock wave, Curved leading edges, delta wings, Hypersonic, Pitching derivatives
Subjects: 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: 11 Apr 2016 11:56
Last Modified: 12 Jun 2018 11:39
URI: http://irep.iium.edu.my/id/eprint/49938

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