弧形翼-身组合体零攻角流场的数值仿真研究

Numerical Simulation of Flowfield of Projectile with WAF at Zero Angle of Attack

通过有限体积法和二阶迎风格式,对弧形翼-身组合体流场进行了数值仿真研究。研究结果给出了弧形翼气动特性随飞行马赫数[Ma=1.5～5.5]的变化,其静态稳定性的损失变化和滚转力矩系数的变化规律,且详细分析了弧形翼在零攻角下产生自诱导滚转力矩的原因。数值计算结果与国外的风洞实验结果进行比较,发现与JPL飞行实验有较好的吻合性。

TheflowfieM of projectile with wrap-aroundfins was numerically investigated at supersonic Mach numbers （1.5- 5.5）using finite volume method and 2nd upwind scheme. Investigating results indicate the loss of static stability and the variety of roll moment coefficient with increasing flighting Mach numbers. Possible sources of self-induced rolling moment at zero angle of attack were analyzed. Computational results show good agreement with experimental results obtained in JPL flight test.