NUMERICAL-SIMULATION OF HEAT-TRANSFER IN CHEMICALLY REACTING SHOCK WAVE-TURBULENT BOUNDARY-LAYER INTERACTIONS

The flow field of a transverse jet in a supersonic airstream subjected to shock wave-turbulent boundary layer interactions is simulated nume rically by adaptive mired explicit-implicit generalized-Galerkin finit e element methods. In this scheme, convection and diffusion implicitne ss parameters are introduced to resolve shock wave discontinuities and widely disparate time and length scales of turbulence and finite rate chemistry. These parameters are flow field dependent, calculated from local Mach, Reynolds, and Damkohler numbers for each element. Effects of turbulence are taken into account with a two-equation (kappa-epsil on) model with a compressibility correction. Various cases of mixing, slot widths, and fetal pressure ratios with and without chemical react ions are examined. Favorable comparisons with experimental measurement s are demonstrated.