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Direct Numerical Simulation of supersonic Boundary Layer Stabilization Using Grooved Wavy Surface
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
Two-dimensional direct numerical simulation (DNS) of stabilization of supersonic boundary layers over a shallow grooved wavy plate at Mach=5.9 is carried out. Numerical experiments are conducted for propagation of disturbances generated by a suction-blowing actuator placed on the wall. Numerical data obtained for a flat plate are consistent with the linear stability theory (LST) and stability experiments in the "Transit-M" wind tunnel of the Institute of Theoretical and Applied Mechanics. It isdoi:10.2514/6.2010-1245 fatcat:j2zgyeiq65bktdax6o2l5gvklu