Advanced Mixing Control in Supersonic Airstream with a Wall-Mounted Cavity

The acoustic wave impinging effect on the initial condition of the supersonic mixing layer growth is investigated. The flow at the 2D nozzle exit was shown with the axes whose origin was set on the center of the injector exit. Near the injector exit, an expansion fan followed by a recompression wave is observed. From the observation, the oscillation was caused by the same oscillation of the mixing layer in the synchronized image along with the instantaneous one. When the fluctuations of the beam intensity passing through the mixing layer were detected downstream, nearly the same fundamental frequency with the acoustic disturbance was obtained.