Numerical Investigations of Aeroheating for Missile Slots

Abstract

A hypersonic aeroheating numerical simulation method for the missile slot flow in the conditions of high temperature and thermochemical nonequilibrium is carried out. The finite-volume method for solving Navier-Stokes equation based on the second-order accuracy upwind scheme is employed in the multiply blocked structure grid solver. The solver includes Park’s two-temperature model and the air multispecies reaction model. The derivation of the total variation diminishing (TVD) formulation with second-order accuracy is implemented in order to improve the efficiency of the hypersonic aeroheating computations. From the comparison between the results of the presented numerical method and the existing experiment data, it can be concluded that the proposed method can provide encouraging computational accuracy.