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A computational investigation of laminar shock/wave boundary layer interactions

Published online by Cambridge University Press:  27 January 2016

N. R. Deepak,
S. L. Gai and
A. J. Neely
N. R. Deepak*
Affiliation:
School of Engineering and Information Technology, The University of New South Wales, Australian Defence Force Academy, Canberra, Australia
S. L. Gai
Affiliation:
School of Engineering and Information Technology, The University of New South Wales, Australian Defence Force Academy, Canberra, Australia
A. J. Neely
Affiliation:
School of Engineering and Information Technology, The University of New South Wales, Australian Defence Force Academy, Canberra, Australia
*
deepak.narayan@gmail.com
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Abstract

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Hypersonic laminar flow past a compression corner has been numerically investigated using time-accurate computational fluid dynamics (CFD) approach. Two flow conditions were considered relevant to high and low enthalpy conditions with a total specific enthalpy of 19MJ/kg and 2·8MJ/kg. The Mach number and unit Reynolds number per metre were 7·5, 9·1 and 3·10 × 105 and 32·2 × 105 respectively. These free stream conditions provided attached, incipiently separated and fully separated flows for ramp angles between θw = 5° to 24°. A grid independence study has been carried out to estimate the sensitivity of heat flux and skin friction in the strong interaction regions of the flow. The investigation was carried out assuming the flow to be laminar throughout and high temperature effects such as thermal and chemical nonequilibrium are studied using Park’s two temperature model with finite rate chemistry. A critical comparison has been made with existing steady state computational and experimental data and the study has highlighted the importance of high temperature effects on the flow separation and reattachment.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1187 , January 2013, pp. 27 - 56
Copyright
Copyright © Royal Aeronautical Society 2013 

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