NUMERICAL SIMULATION FOR HYPERSONIC FLOW OF NONEQUILIBRIUM GASES AROUND THE APOLLO COMMAND MODULE

A hybrid flux splitting method is used to develop an implicit NND scheme which possesses good stability characteristics and high converging velocity. The hypersonic flows of the perfect gas and nonequilibrium gas around the Apollo Command Module are simulated with the method by solving the N-S equations. The numerical results agree with the experimental data satisfactorily. The flow structure in the leeside and wake is studied with the topological method.