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DNS ANALYSIS OF SHOCK WAVE / TURBULENT BOUNDARY LAYER INTERACTION AT M = 2.25

Sergio Pirozzoli
Dipartimento di Meccanica e Aeronautica, Universita di Roma 'La Sapienza' Via Eudossiana 18, 00184 Roma, Italy

Francesco Grasso
Dipartimento di Meccanica e Aeronautica, Universita di Roma 'La Sapienza' Via Eudossiana 18, 00184 Roma, Italy

Thomas B. Gatski


Abstrakt

In this study the interaction of a supersonic flat plate boundary layer flow with an impinging shock (at M = 2.25 and Reθ ~ 4000, and shock angle β = 32.7°) is analyzed by means of a direct numerical simulation. The results show that under such conditions, the flow field dynamics upstream of the impinging shock closely resembles the incompressible pattern; however, in the interaction zone the flow undergoes separation due to the adverse pressure gradient, and the recovery of the universal behavior occurs on a length scale of 0(10δo), where is the boundary layer thickness in the absence of the interaction. The simulations also clearly suggest severe flapping motion of the reflected shock past the interaction zone, with the generation of sound waves. The results also indicate that the localized turbulence amplification is mainly related to the formation of large vortical structures associated with boundary layer separation.