Abstract

A hypersonic viscous shock layer over a flat plate at the free-stream Mach number M∞ = 21 is investigated both numerically and experimentally. The shock layer is excited by either external acoustic field or blowing/suction on the plate surface. The interaction of disturbances with the leading edge shock wave and their development in the boundary layer are simulated by solving the Navier-Stokes equations with a high-order shock-capturing scheme. Data of numerical simulations are compared very favorably with measurements conducted in a hypersonic nitrogen wind tunnel using the electron-beam fluorescence techniques. Numerical simulations show that the interference between natural and artificially excited disturbances can be used for active control of the instability development. This conclusion is confirmed experimentally.

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