摘要
采用有限体积法对积分形式的Navier Stokes方程组进行空间离散,所获得的常微分方程用多步Runge Kutta方法求解。数值模拟了某导弹冲压发动机进气道的三维流场,给出了不同反压条件下该进气道的内外流场结构和表面压强分布,并分析了进气道内激波与附面层的相互作用现象。
The Navier-Stokes equations in the integral form are spatially discretized using finite volume method. The obtained ordinary differential equations are solved using multistage Runge-Kutta method. A three-dimensional ramjet inlet flow field is calculated. The flow field structures and surface pressure distributions of the inlet at the different backpressures are given. The interactions of shock waves and boundary layers are analyzed.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2003年第4期30-33,共4页
Journal of Solid Rocket Technology
