Numerical Simulation of Transverse H_2 Combustion in Supersonic Airstream in a Constant Area Duct

摘要

Reacting flow field of H_2-air combustion behind a backward facing step in a constant area combustor is simulated numerically by solving three-dimensional Navier Stokes equations along with K-ε turbulence model and fast rate chemistry. Simulation captures all the essential features of the flow field. The computed surface pressures match extremely mell with the results of other numerical computations for non-reacting flow. For reacting case, although a good match obtained in the downstream, present computation over predicts the surface pressure.