大迎角细长体非对称空间流场特性的试验研究  

Investigation of flow field characteristics on aslender body at high angle of attack

作　　者：顾蕴松[1] 明晓[1] 

机构地区：[1]南京航空航天大学空气动力学系,南京210016

出　　处：《实验流体力学》2005年第2期1-6,共6页Journal of Experiments in Fluid Mechanics

摘　　要：应用七孔探针定量流场测试技术,在低速风洞中通过定量测试细长旋成体背风区三维空间流场,研究了零侧滑条件下细长旋成体在典型大迎角情况下(迎角为55°)背风区附体和离体涡系的空间演化规律,加深了对细长旋成体背风区不对称涡系空间结构的认识。解释了截面侧向力沿模型体轴分布为幅值递减波形的形成机制。给出了有、无头部小扰动片及小扰动片非定常摆动控制三种情况下的细长体背风区不同的多涡空间结构。细长旋成体背风区横截面的涡量和总压分布测量结果表明在模型头部固定小扰动片可以改变非对称涡的非对称特性,但不能使非对称涡变为对称涡,而在头部非定常小扰动的控制下模型背风区流动呈现对称涡的流态特征。In this paper, we present the results of experimental investigations on the flow field around a conventional sharp-nose ogive cylinder model at high angles of attack (α=55°). The studies include simultaneous side-force and flow field measurements in a low-speed close circuit wind tunnel at the cases of with and without forebody vortices control. The cross plane flow field at different axial positions on the lee-ward of the model were scanned by a seven hole probe. The results show the asymmetric vortices on the slender body with steady nose-tip strake control and the symmetric flow pattern can not achieved in this case. The vorticity contour map and the total pressure coefficient contour map revealed the symmetric vortex flow pattern under the unsteady micro perturbation control.

关 键 词：细长体 大迎角 试验研究 流场特性 对称空间 细长旋成体 空间结构 非对称涡 小扰动 测试技术 七孔探针 空间流场 定量测试 低速风洞 演化规律 形成机制 摆动控制 分布测量 非定常 风区 不对称 模型体 侧向力 头部 横截面 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V211.4