钝头飞行器大攻角绕流流场计算

本文用有限差分法求解Ｎ－Ｓ方程，对具有大面积底部飞行器的高超声速大攻角绕流流场进行了计算，通过积分物面压力给出了飞行器的气动力特性，并研究了攻角的影响，物面压力系数和气动力系数与实验数据进行了比较，符合较好，结果可应用到返回舱和弹头的再入气动特性研究。

The Flowfield Calculation for a Blunt Vehicle at Large Angle of Attack

Using finite difference method solving N-S equations,thehypersonic flows over a vehicle with large area bottom at high incidenceare calculated.From integrating surface pressure,the aerodynamic char-acteristics of vehicle are given.The effects of angles of attack on flow andaerodynamic characteristics are studied.Finally the calculations are com-pared with experimental data, and good agreement is reached.