Numerical Simulation of the Supersonic Boundary Layer Interaction with Arbitrary Oriented Acoustic Waves

Based the direct numerical simulation in the paper the supersonic flow around of the infinitely thin plate, which was perturbed by the acoustic wave, was investigated. Calculations carried out in the case of small perturbations at the Mach number M=2 and Reynold's numbers Re<600. It is established that the velocity perturbation amplitude within the boundary layer is greater than the amplitude of the external acoustic wave in several times, the maximum amplitude growth is reached 10. At the small sliding and incidence angles the velocity perturbations amplitude increased monotonously with Reynold's numbers. At rather great values of these angles there are maxima in dependences of the velocity perturbations amplitude on the Reynold's number. The oscillations exaltation in the boundary layer by the sound wave more efficiently if the plate is irradiated from above. At the fixed Reynolds's number and frequency there are critical values of the sliding and incidence angles (chi, phi) at which the disturbances excited by a sound wave are maxima. At M=2 it takes place at chi approximate to phi approximate to 30 degrees. The excitation efficiency of perturbations in the boundary layer increases with the Mach number, and it decreases with a frequency.