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Understanding of flow features over a typical crew module at Mach 4

Published online by Cambridge University Press:  27 January 2016

S. L. N. Desikan ,
M. M. Patil  and
S. Subramanian
M. M. Patil
Affiliation:
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram, India
S. Subramanian
Affiliation:
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram, India
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Abstract

This paper presents the numerical simulations of flowfield over a typical Crew Module at Mach 4 for different angles-of-attack ranging from 0 to –25°. Detailed flow features such as contour of density gradient over the model, numerical oil flow and near wake vortex structures are captured very well in the present simulations. The location of the sonic line and its behaviour due to angles-of-attack is also captured in the simulations. The CP distribution on the windward and leeward side shows excellent match with the experimental results. Also, the prediction of aerodynamic coefficients shows very good agreement with the experimental results. The numerical simulation predicts CMcg, CN and CA within 8%, 4% and 3·5% respectively with respect to experimental values.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1216 , June 2015 , pp. 727 - 746
Copyright
Copyright © Royal Aeronautical Society 2015

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