钝头旋成体背涡迎角效应的分区性态  

Zonal behavior of angle of attack effects on vortices over blunt-slender body

作　　者：齐中阳 王延奎[1,2] 曹鹏 QI Zhongyang;WANG Yankui;CAO Peng(State Key Laboratory of Aerodynamics,Mianyang 621000,China;School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100083,China;Shanghai Institute of Spaceflight Control Technology,Shanghai 200233,China)

机构地区：[1]空气动力学国家重点实验室,绵阳621000 [2]北京航空航天大学航空科学与工程学院,北京100083 [3]上海航天控制技术研究所,上海200233

出　　处：《北京航空航天大学学报》2018年第10期2134-2140,共7页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(11472028;11721202);空气动力学国家重点实验室开放基金(SKLA20160101);航空科学基金(2016ZA51)~~

摘　　要：为了实现空空导弹的高机动性,基于模型后体直径D以及试验风速的雷诺数Re_D=1.54×10~5,通过风洞测力和测压试验对钝头旋成体背涡流动特性随迎角的演化形式进行了研究。根据对模型不同迎角下所受侧向力、截面压力分布以及截面侧向力系数随时间波动情况的分析,确定了不同迎角下的钝头旋成体背涡流动形式。以此划分了4个迎角分区:附着流动区(α≤10°)、对称涡流动区(10°<α≤20°)、定常非对称流动区(20°<α≤50°)和非定常非对称流动区(α>50°)。对各迎角分区的背涡流动特性进行了详细讨论。In order to achieve the high maneuverability of the air-to-air missile,the flow characteristics of vortices over the blunt-slender body at different angles of attack were studied by wind tunnel forces and pressure test in this paper. The Reynolds number is set as ReD= 1. 54 × 10^5,based on oncoming free-stream velocity and the diameter of the blunt-slender body（ D）. The flow structures over the blunt-slender body were determined at different angles of attack according to the analysis of side forces,sectional pressure distribution and the variation histories of the sectional side force with time. Four regions about the angles of attack are divided,i. e.,attached-flow region（ α≤10°）,symmetric-flow region（ 10° α≤20°）,steady asymmetric-flow region（ 20° α≤50°） and unsteady asymmetric-flow region（ α 50°）. The flow characteristics of vortices over the blunt-slender body at different angles of attack were discussed in detail.

关 键 词：钝头旋成体 背涡结构 迎角效应 非对称流动 大迎角空气动力学 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]