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Pressure sensitive paint measurements on a delta-wing in supersonic flow

Published online by Cambridge University Press:  03 February 2016

L. C. Raju ,
L. Venkatakrishnan  and
P. R. Viswanath
L. C. Raju
Affiliation:
Experimental Aerodynamics Division, National Aerospace Laboratories, Bangalore, India
L. Venkatakrishnan
Affiliation:
Experimental Aerodynamics Division, National Aerospace Laboratories, Bangalore, India
P. R. Viswanath
Affiliation:
Experimental Aerodynamics Division, National Aerospace Laboratories, Bangalore, India
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Abstract

Experiments have been performed documenting the pressure field on the lee-side of a delta-wing at three incidence angles (5°, 10°, and 15°) and at Mach 1·8 using a PSP (Pressure Sensitive Paint) technique. The delta-wing model having a leading edge sweep of 60° was instrumented with 31 spanwise pressure ports at 68% of mean chord location. The Optrod-B1 binary paint was utilised and the PSP images were processed employing a resection based methodology. The comparisons of PSP results with those measured employing pressure taps show good agreement at different incidence angles.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1113 , November 2006 , pp. 767 - 771
Copyright
Copyright © Royal Aeronautical Society 2006 

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