The flow transition in a shock wave boundary layer interaction (SVVBLI), which is simulated by performing direct numerical simulation (DNS), is controlled by a passive and an active surface morphing technique. The SWBLI comprises a laminar boundary layer evolving from a Blasius profile at Mach 2 and Reynolds number based on inflow boundary layer thickness of Re_(δin) = 996 that interacts with an incident oblique shock with shock angle (σ) and strength (p3/p1) of 35deg and 1.4 respectively. The uncontrolled transitional SWBLI results in the flow separation and gives rise to unsteady three-dimensional flow structures, which comprise the streamwise-oriented (Gortler like) vortex pairs. Furthermore, the SWBLI exhibits the characteristic low frequency oscillations of the separation bubble. In order to mitigate the flow separation and associated unsteadiness without incurring additional loss of the stagnation pressure, the control surface beneath the SWBLI is deformed statically and dynamically. In the passive control approach, the control surface is deformed into the flow domain to form a static shock control bump (SCB); whereas in the active flow control strategy, a more generic framework is developed for adaptive surface morphing anticipating an optimal surface deformation. The application of control to the transitional SWBLI inhibits the flow transition and flow separation, resulting in a steady SWBLI.
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