超音速气流中横向喷射氢气流场数值模拟

THE NUMERICAL MODEL OF SUPERSONIC AIR FIOW FIELD WITH HYDROGEN TRANSVERSE INJECTION

关键词:  超音速燃烧  流场  数值解

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

摘要:

本文通过应用Mac Cormack显式时间分裂法和Baldwin-Lomax修正的代数湍流模型求解二维可压缩的N-S方程和混气组分方程,对超音速气流中横向喷入氢气后的流场进行了数值模拟。计算结果示出了流场中速度矢量分布,静压、静温和氢气质量分数的等值线分布,反映出了喷嘴附近流场回流区的大小及可能的点火位置,从而为超燃冲压发动机的设计工作提供理论指导。

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.