NUMERICAL INVESTIGATION OF TWO-PHASE GASPARTICLE

ow over a body Abstract. The paper describes the results of computational simulation of an unsteady two-phase gas-particle ow in a hypersonic shock tunnel. The tunnel consists of a heated shock tube, a convergent-divergent nozzle linked up with the low-pressure chamber of the tube, a test section where a model is placed, and a exhaust chamber. In calculations, the conguration of the tunnel, and the initial parameters in the high-pressure and low-pressure chambers of the shock tube were taken as in experiments carried out at TsAGI (Russia). The designed Mach number at the nozzle exit was equal to M = 6.01. Particles were injected into the high-pressure chamber of the shock tube just before the diaphragm destructed. Their initial concentration was very low, so that the reverse effect of the dispersed phase on the carrier gas was negligible. The carrier gas ow was described by the Euler equations which were solved by the nite-volume method of the second order. In the calculation domain, an unstructured grid was used with a high concentration of nodes near the critical cross-section of the nozzle and in the vicinity of the body in the test section. Triangular and polygonal nite-volume cells were taken. The uxes at cell boundaries were calculated using four different algorithms of the TVD-type. The best quality of the numerical solution for the ow eld was obtained with the use of the modied second-order Godunov method for uxes applied to the polygonal cells. The particle-phase ow was simulated using the Lagrangian method. A ne structure of two-phase ow was investigated from the instant of destruction of a diaphragm between high- and low-pressure chambers of the shock tube to the end of the quasi-steady-state ow over a body in the test section.