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Sebastien Piponniau
Institut PPRIME, UPR 3346 CEAT, 43, rue de l'aerodrome 86000 Poitiers, France; Aix Marseille Univ CNRS, IUSTI 13453 Marseille cedex 13, France

Erwan Collin
Laboratoire d'Etudes Aérodynamiques, UMR CNRS 6609 - Université de Poitiers - ENSMA CE.A.T., 43, route de l'Aérodrome F-86036 Poitiers - France

Pierre Dupont
IUSTI Aix-Marseille University, UMR CNRS 7343 13453 Marseille Cedex 13, France

Jean-francois Debieve
IUSTI, UMR CNRS 6595 5, Rue Enrico Fermi 13453 Marseille Cedex 13, France


We present here experimental results in a shock wave / turbulent boundary layer interaction at Mach number of 2.3 impinged by an oblique shock wave, with a deflection angle of 9.5°, as installed in the supersonic wind tunnel of the IUSTI laboratory, France. For such a shock intensity, strong unsteadiness are developing inside the separated zone involving very low frequencies associated with reflected shock motions, together with a mean three dimensional organization of the flow.
The present work consists in simultaneous PIV velocity fields and unsteady wall pressure measurements. The wall pressure and PIV measurements were used to characterize the pressure distribution at the wall in an axial direction, and the flow field associated. These results give access for the first time to the spatial-time correlation between wall pressure and velocity in a shock wave turbulent boundary layer interaction and show the feasibility of such coupling techniques in compressible flows. Linear Stochastic Estimation (LSE) coupled with Proper Orthogonal Decomposition (POD) has been applied to these measurements, and first results are presented here show the ability of these techniques to predict the unsteady breathing of the recirculating bubble.