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Comparisons between low Reynolds number two-equation models for computation of a shockwave-turbulent-boundary layer interaction

Published online by Cambridge University Press:  04 July 2016

B. K. Yoon,
M. K. Chung and
S. O. Park
B. K. Yoon
Affiliation:
Examination Bureau II, Korea Industrial Property Office Kangnam-ku, Seoul, Korea
M. K. Chung
Affiliation:
Department of Mechanical Engineering, Korea Advanced Institute of Science and Technology Yusong-ku, Taejon, Korea
S. O. Park
Affiliation:
Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology Yusong-ku, Taejon, Korea
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Abstract

A comparative study is made on the performance of several low Reynolds number k-ε models and the k-ω model in predicting the shockwave-turbulent-boundary layer interaction over a supersonic compression ramp of 16°, 20° and 24° at a Mach numbers of 2.85, 2.79 and 2.84, respectively. The model equations are numerically solved by a higher order upwind scheme with the 3rd order MUSCL type TVD. The computational results reveal that all of the low Reynolds number k-ε models, particularly those employing y+ in their damping functions give erroneously large skin friction in the redeveloping region. It is also interesting to note that the k-ε models, when adjusted and based on DNS data, do not perform better, as expected, than the conventional low Reynolds number k-ε models. The k-ω model which does not adopt a low Reynolds number modification brings about reasonably accurate skin friction, but with a later onset of pressure rise. By recasting the ω equation into the general form of the ε equation, it is inferred that the turbulent cross diffusion term between k and ε is critical to guarantee better performance of the k-ω model for the skin friction prediction in the redeveloping region. Finally, an asymptotic analysis of a fully developed incompressible channel flow, with the k-ε and the k-ω models, reveals that the cross diffusion mechanism inherent in the k-ω model contributes to the better performance of the k-ω model.

Information

Type
Technical Note
Information
The Aeronautical Journal , Volume 101 , Issue 1007 , September 1997, pp. 335 - 345
Copyright
Copyright © Royal Aeronautical Society 1997 

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