摘要
栅格翼是由外部框架和内部栅格布置形成的空间多升力面系统,其在高超声速状态具有突出优点。文中结合高超声速流动特点,考虑头部激波及弹身上洗干扰,基于面元法建立栅格翼翼身组合体高超声速气动特性计算模型,根据研究对象特点自动划分面元,进而完成典型栅格翼翼身组合体高超声速气动特性计算,并与数值计算结果进行对比分析。结果表明,在研究范围内,栅格翼翼身组合体高超声速气动特性面元法计算结果与数值计算结果吻合较好,前者较后者相对误差绝对值随攻角增加而增大。
Grid fin is a space lifting surface formed by the external frame and internal web ,which is of outstanding advantages in hypersonic state. Hypersonic aerodynamic characteristics analysis model of grid fin-body configuration is established based on sur- face element method considering the characteristics of hypersonic flow, the head shock wave and body upwash interference were taken into account as well. Surface element was built automatically according to grid fin-body configuration geometry feature. Grid fin-body configuration hypersonic aerodynamic characteristics were obtained and agreed well with numerical results. The deviation increases with angle of attack.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第4期442-445,共4页
Journal of Solid Rocket Technology
关键词
栅格翼
高超声速
气动特性
面元法
grid fin
hypersonic
aerodynamics character
surface element modeling
