Abstract
An experimental study of the structure of wall pressure fluctuations is performed in shock-induced separated supersonic turbulent flows. Two test conditions are studied for external Mach numbers of 2.25 at low Reynolds number and Mach 3.3 at high Reynolds number. Piezoelectric pressure transducers, isolated from the main facility to minimize vibration effects, are used to sense the pressure fluctuations. Pressure fluctuations are given for several locations and analyzed in the frequency domain. The results exhibit the usual behavior. Space-time correlations are measured and subsequently analyzed using coherence analysis. The results are discussed in terms of structural modifications induced by the shock. Typical results are given for several positions in the incoming boundary layer, at the mean shock location, and in the recirculation region. Some new features concerning the behavior of characteristic scales at the shock traverse are identified, and the results are compared and scaled for both test conditions.
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