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Experimental study of overexpanded supersonic jet impingement on a double wedge deflector

Published online by Cambridge University Press:  04 July 2016

J.K. Prasad ,
R.C. Mehta  and
A.K. Sreekanth
J.K. Prasad
Affiliation:
Vikram Sarabhai Space Centre, Trivandrum, India
R.C. Mehta
Affiliation:
Vikram Sarabhai Space Centre, Trivandrum, India
A.K. Sreekanth
Affiliation:
Indian Institute of Technology, Madras, India
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Abstract

Experiments have been conducted to study the impingement fiowfield, over a double wedge deflector, produced by the impingement of an overexpanded supersonic jet. The jet has an exit Mach number of 3.1 and an expansion ratio of 0.81. The distance between the nozzle exit and deflector apex was varied from 2 to 5 times the nozzle exit diameter. The experiment consisted of schlieren flow visualisations and measurements of pressure distribution. Load coefficient has been obtained by integrating the measured pressure distributions. Boundary layer thickness and skin friction coefficient on the deflector surface have been calculated by solving compressible turbulent boundary layer equations, using moment integral and moment-of-momentum integral equations in conjunction with the measured surface pressure distributions.

Type
Research Article
Information
The Aeronautical Journal , Volume 97 , Issue 966 , July 1993 , pp. 209 - 214
Copyright
Copyright © Royal Aeronautical Society 1993 

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