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

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.