实验流体力学Issue(6)：6-13,8.
高速下模型头部扰动与非对称涡流动响应研究
摘要
Abstract
Using pointed tangent-ogive slender body,under the Mach number ranged from 0.4 to 1.2,and angle of attack ranged from 0°to 50°,the pressure measure tests and PIV tests were completed in high speed wind tunnel to investigate the response between model tip perturba-tion and asymmetric vortex flow at high angles of attack.The results show that asymmetric multi-vortex flow structures still exist in high speed case.It was observed that there was a distinct relation between tip perturbation and response of asymmetric vortex flow,but a feeble relation between tip perturbation and response of asymmetric aerodynamic force.关键词
大迎角空气动力学/非对称流动/压缩性/头部扰动/风洞实验Key words
high angle of attack aerodynamics/asymmetric vortex/compressibility/nose per-turbation/wind tunnel test分类
航空航天引用本文复制引用
贺中,吴军强,蒋卫民,吴继飞..高速下模型头部扰动与非对称涡流动响应研究[J].实验流体力学,2013,(6):6-13,8.基金项目
国防预研基金 （）
