28th Congress of the International Council of the Aeronautical Sciences, 23 - 28 September 2012, Brisbane, Australia
VISUALIZATION OF UNSTEADY BEHAVIOR OF SHOCK WAVES AROUND SUPERSONIC INTAKE INSTALLED IN SHOCK TUNNEL
N. Tanaka, T. Mizukaki
Tokai Univ., Japan
Keywords: supersonic intake, buzz, shock tunnel, flow visualization, pressure-sensitive paint
The purpose of this study is to quantitatively visualize unsteady behavior of shock waves (buzz) and boundary layer by anodized aluminum pressure-sensitive paint (AA-PSP). From the results of surface pressure distribution and shock wave structures, we clearly confirmed buzz around the supersonic intake model at subcritical state.
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