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Transonic small disturbance unsteady potential flow over very high aspect ratio wings

Published online by Cambridge University Press:  11 February 2022

J. R. Kwon  and
R. Vepa Open the ORCID record for R. Vepa [Opens in a new window]
J. R. Kwon
Affiliation:
Aerospace Technology Research Institute, Agency for Defense Development, Daejeon, 34186, Republic of Korea
R. Vepa*
Affiliation:
School of Engineering and Material Science, Queen Mary, University of London, London, E14NS, UK
*
Email: [email protected]
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Abstract

In this paper, the prediction of the unsteady flow field over typical high aspect ratio (AR) wings in the transonic flow regime but below the sonic Mach number is of interest. The methodology adopted is a computational approach based on the transonic small disturbance unsteady potential equation. It is shown that the higher AR wings generally have a higher lift coefficient as well as a higher lift-to-drag ratio. With NASA’s common research model (CRM) wing, there is an increase in maximum lift with increasing AR while the induced drag is almost the same. There is also an optimum sweep angle, which is different for each angle-of-attack so that variable sweep lifting surfaces may be designed to provide optimum solutions. The computed flutter speeds indicate an expected reduction with increasing AR.

Keywords

Unsteady transonic flowPotential flowFull potential equationTransonic small disturbanceHigh aspect ratio wings
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1305 , November 2022 , pp. 1834 - 1852
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Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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