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Numerical simulation of ramp induced shock wave/boundary-layer interaction in turbulent flow

Published online by Cambridge University Press:  27 January 2016

Asmelash H. A. ,
R. R. Martis  and
A. Singh
Asmelash H. A.*
Affiliation:
Aeronautical Engineering Department, Defence University, College of Engineering, Ethiopia
R. R. Martis
Affiliation:
Department of Aerospace Engineering, Defence Institute of Advanced Technology, India
A. Singh
Affiliation:
Terminal Ballistics Research Laboratory (TBRL), Chandigarh, India
*
[email protected], [email protected]
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Abstract

A computational study has been carried out to analyse the shock wave turbulent boundary layer interaction in a two-dimensional compression ramp flow for a free stream Mach number of 2·94. Ramp angles ranging from 8° to 24° are used to produce the full range of possible flow fields, including flows with minor separation, moderate separation, and significant amount of separation. The model has been analysed using 2D numerical simulations based on a commercially available Computational Fluid Dynamics (CFD) Code, Fluent, that employs k-ω Shear Stress Transport (SST) turbulence model. The computed data for surface pressure distribution indicated a good agreement with experiment. Numerical results obtained through the present series of computations indicate an increased extent of separated zone, and thus show increased upstream influence when compared to experiment. Total pressure loss has shown to increase downstream of separation location and increase when corner angle increases. Secondary separation has been observed for higher angles.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1192 , June 2013 , pp. 629 - 638
Copyright
Copyright © Royal Aeronautical Society 2013 

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References

1. J.M., Delery. Shock Wave Turbulent Boundary Layer Interaction and its Control, Aerospace Sci, 1985, 22, pp 209–280.Google Scholar
2. Settles, G.S., Fitzpatrick, T.J. and Bogdonoff, S.M. A detailed study of attached and separated compression corner flow-fields in high Reynolds number supersonic flow, AIAA J, 1978, 17, (6), pp 579–585.Google Scholar
3. Arnal, D. and Delery, J. Shock Wave Boundary Layer Interaction, NATO, May 2004.Google Scholar
4. Oliver, , et al Assessment of Turbulent Shock-Boundary Layer Interaction Computations Using the OVERFLOW Code, School of Aeronautics and Astronautics, Purdue University, January 2007.Google Scholar
5. Settles, G.S. and Dodson, L.J. Hypersonic Shock/Boundary Layer Interaction Database: New and Corrected Data, NASA Contractor Report 177638, April 1994.Google Scholar
6. Kuntz, D.W. et al Turbulent Boundary Layer properties downstream of the Shock-Wave/Boundary Layer interaction, AIAA J, May 1987, 25, (5).Google Scholar
7. Wilcox, D.C. Turbulence Modeling for CFD, DCW Industries, California, USA, 1994.Google Scholar
8. Asmelash, H. A. and Singh, A. Numerical Analysis of Shock Wave Turbulent Boundary Layer Interaction over a 2D Compression Ramp, (IJAEST) Int J Advanced Engineering sciences and Technologies, April 2011, 5, (2), pp 144–149.Google Scholar