钝头飞行器大攻角绕流流场计算  

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

作　　者：周伟江[1] 汪翼云[1] 

机构地区：[1]北京空气动力研究所

出　　处：《空气动力学学报》1995年第2期200-204,共5页Acta Aerodynamica Sinica

摘　　要：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。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.

关 键 词：再入飞行器 近尾迹 数值计算 绕流流场 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]