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Triple-deck solutions for viscous supersonic and hypersonic flow past corners

Published online by Cambridge University Press:  19 April 2006

D. P. Rizzetta ,
O. R. Burggraf  and
Richard Jenson
D. P. Rizzetta
Affiliation:
Department of Aeronautical and Astronautical Engineering, The Ohio State University, Columbus, Ohio 43210 Present address: The Boeing Company, Seattle, Washington.
O. R. Burggraf
Affiliation:
Department of Aeronautical and Astronautical Engineering, The Ohio State University, Columbus, Ohio 43210
Richard Jenson
Affiliation:
Department of Aeronautical and Astronautical Engineering, The Ohio State University, Columbus, Ohio 43210 Present address: Department of Aerospace Engineering, Texas A & M University, College Station, Texas 77840.
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Abstract

A viscous-inviscid interaction is produced when a compressible laminar boundary layer encounters a corner. The correct mathematical structure for such interactions at large Reynolds number is given by the asymptotic triple-deck theory. In the present work the triple-deck equations for supersonic and hypersonic flows are solved for both compression and expansion corners. Results are presented for a range of corner angles, including separated cases, and are compared with experimental data and with finite Reynolds number calculations based on an interacting boundary-layer model.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 89 , Issue 3 , 13 December 1978 , pp. 535 - 552
Copyright
© 1978 Cambridge University Press

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