NUMERICAL INVESTIGATION OF MIXING AUGMENTATION BEHIND OBLIQUE SHOCK-WAVES

The interaction of st three-dimensional supersonic turbulent jet with an oblique shock wave and a system of shocks in a hypersonic inlet is numerically investigated. The flow is simulated by the parabolized Navier-Stokes equations and a one-equation turbulence model. It is shown that jet convergence behind the single shock leads to an increase of mixing on the order of 2-4 times. The system of shocks in the hypersonic inlet increases the mixing of air and helium Injected before the inlet entrance. The mixing completeness at the inlet throat reaches a value of about 0.6-0.7 without significant pressure loss. A simplified technique for estimating the maximum concentration in a jet behind a shock is proposed. The results obtained with the help of this technique agree rather well with the numerical data.