Abstract
The influence of supersonic flow parameters on the spectral density of surface pressure fluctuations associated with shock/boundary-layer interaction has been investigated experimentally. The main methodological problems with the wind tunnel experiments are presented as are the experimental facility, measurement methods, models and devices. A wide range of shock angles of incidence, Mach numbers and Reynolds numbers were used. Increase in the shock intensity is accompanied by sharp intensification of pressure fluctuations in the interaction region and by an expansion of the zone of increased pressure fluctuations. This sharp intensification occurs only in the region of low and moderate Strouhal numbers. For high Strouhal numbers, where there is a strong dependency of pressure-fluctuation intensity on Strouhal number, practically no influence of the shock intensity itself is observed. The experimental results indicate a weak influence of Mach number on pressure fluctuations at constant shock angle. The influence of Reynolds number is weak for large values.
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