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This paper investigates jets injection into supersonic main flow, where the jets are surrounded by the porous cavity. This application of the porous cavity to the jet injection aims for the supersonic mixing enhancement. Supersonic mixing technique is important for scramjet engines to improve combustion efficiency. This method using porous cavity has been experimentally studied. However, it is difficult experimentally to measure the mixing efficiency, total pressure loss, and a circulation between the main flow and the cavity flow. Therefore, this paper numerically studies this flow field. In the calculation, Navier-Stokes equations were solved using AUSMDV scheme with 3rd order MUSCL scheme and the four stage Runge-Kutta scheme. Two cases, with the porous cavity and without the porous cavity, were calculated. As a result, a circulation between the main flow and the porous cavity is confirmed. Moreover, it is found that the bow shock wave and the dead water region of the jet were the important factors of this circulation. In addition to the circulation, total pressure loss due to the porous cavity was revealed.

Numerical Study of Injected Jets into Supersonic Main Flow from a Porous Cavity