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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
*
ahaftu@yahoo.com, asmilh@gmail.com
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Abstract

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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.

Information

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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