超声速射流对挡流板的冲击流场的数值模拟

采用数值分析方法分析了跨声速喷管无粘流动和超声速射流对挡流板的冲击流场。该方法是对激波流动添加了显式人工粘性项，控制方程仍为Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程，采用ＭａｃＣｏｒｍａｃｋ二阶显式预后－校正差分格式求解。

Numerical Simulation of Supersonic Jet Impingement on a Jet Tabc

Numerical analyses of the transonic nozzle inviscid flow and supersonic jet impingement on a jet tab are presented. Because an explicit artificial viscosity is ineluded for shock calculations, the governig equation are Navier-Stodes equations which are solved using the MacCormack second-order, explieit, prdictioncorrction,finite-difference scheme. Boundary mesh points are calculated using a reference-plane characteritic scheme with the viscous terms treated as source furctions. The steady-state solution is obtained as the asymptoitic solution converges for a long time using time-dependent mehtod. Some nonuniform initial sata By calcultions of the transonic nozzle fowifield of several sample motors and using their results as input data for jet calcultion, the factors relative to drag ereated by the jet tab and the supersonic jet impingement on the jet tab calculated to obtain the drag.The results indicate that the head-on wind area of the tab is the main factor in determining the drag size.