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

作　　者：郑健[1] 周长省[1] 张磊[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《系统仿真学报》2008年第13期3401-3403,3419,共4页Journal of System Simulation

摘　　要：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.

关 键 词：弧形翼 数值模拟 翼-身组合 区域法 有限体积法 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]