高速下模型头部扰动与非对称涡流动响应研究  

Investigation on response between model tip perturbation and asymmetric vortex flow over slender body in high speed

作　　者：贺中[1] 吴军强[1] 蒋卫民[1] 吴继飞[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2013年第6期6-13,共8页Journal of Experiments in Fluid Mechanics

基　　金：国防预研基金(51313020106)

摘　　要：采用尖拱细长旋成体模型，在M=0．4～1．2范围内，通过表面压力测量和PIV流态观测手段，对高速情况下模型头尖部微扰动与大迎角非对称涡流动的响应关系进行了研究。研究结果表明：在此高速范围内，尖拱细长旋成体的大迎角流动仍然呈现出非对称多涡结构，头部微扰动对非对称涡有影响，但对模型的非对称气动力影响不明显。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 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]