关键词: 超音速燃烧;流场;数值解

Abstract: In this paper, Mac Cormack explicit time-split scheme and Baldwin-Lomax advanced algebraic turbulent model are employed to solve the 2-D compressible N-S and hydrogen equations for numerical simulation of the supersonic air flow field with hydrogen transverse injection. The results show the profiles of the velocity vector, the static pressure contour, the static temperature contour and the hydrogen mass fraction contour, and describe the size of two recirculating zones ahead of and behind bases ofthe jet where ignitionis likely to occur. This capability should provide theory guidance in on going scramjet engine design.

Key words: Supersonic combuston;Supersonic combustion ramjet engi- ne;Flow field;Numerical solution