弧形翼-身组合体空气动力特性的数值模拟研究

利用高精度ＴＶＤ格式成功地完成了标准ＴＴＣＰ弧形翼－身组合体在马赫数为０．８～２．３６的湍流流场计算，通过对翼表面压力的积分求得自诱导转动力矩，与相应的风洞实验数据基本一致。流场的计算结果显示：自诱导转动力矩的变化主要是由于翼前缘和翼后半部分产生的法向力的差异造成的。最后进行了不同翼形参数的弧形翼－身组合体湍流流场计算，发现翼前缘削尖角角度增大和翼弦长增大，使总法向力增大。

Numerical Simulation of Aerodynamic Characteristic of Projectile with WAF

Flow field solutions of TTCP standard WAF is computed for velocities ranging from Mach 0.8 to 2.36 with high accuracy TVD scheme firstly . The roll moment coefficient is obtained from the flow field solutions and in agreement with experiment data. The numerical results reveal that the roll moment is determined by normal forces on forehead fin and after section of fin, and total normal force increases when the fin leading edge become bluntly and the length of fin enlarges at supersonic speed.