• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.409-412
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• 2005

This paper shows the process of Pressure Sensitive Paint(PSP) measurement on the nozzle wall in M=2.5 supersonic wind tunnel, and compare with the result of the paper that performed the PSP measurement in similar condition in NASA Lewis Research Center.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.899-904
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• 2007

During the conceptual design phase of fighter class aircraft, the high speed wind tunnel test with 1/20 scale wing-body-tail model has been conducted to investigate the effects of leading edge flap deflection on the supersonic cruise performance of the aircraft. To select the proper leading edge flap deflection for the wind tunnel test, the aerodynamic characteristics due to various leading edge flap deflections have been analyzed by using corrected supersonic panel method. Based on the results obtained from the experimental and numerical approaches, the effects of leading edge flap deflection have shown to be useful to enhance the supersonic cruise performance of fighter class aircraft.