细长体大迎角非对称流动的高速PIV风洞试验研究  

Study on asymmetric flow over slender body at high angles of attack via Particle Image Velocimetry test in high speed wind tunnel

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,绵阳621000

出　　处：《空气动力学学报》2014年第3期295-299,307,共6页Acta Aerodynamica Sinica

摘　　要：具有细长前体构型的飞行器在大迎角绕流中会出现明显的非对称涡系流动及其伴随而来的非对称力，该现象受多种因素影响，而其中对压缩性效应的研究相对较少。在0．6m 亚跨超声速风洞中，采用 PIV 测量技术，对尖拱细长旋成体大迎角非对称流动开展了试验研究。试验 M 数范围为0．4～1．2，迎角为40°。试验结果表明：细长体模型在高速情况下仍然存在非对称多涡流动结构；Re 数和压缩性均对非对称涡流动产生明显影响；模型头尖部人工微扰动与非对称涡之间存在确定的响应关系。Asymmetric vortex flow and associated side force affects the performance of aircraft with slen-der forebodies flying at high angle of attack,which may happen even when the forebody is axisymmetric and at zero sideslip.This phenomenon can be induced by many factors,the compressibility is one of the posible reasons.This paper primarily focuses on asymmetric vortex flow in high speed.Using pointed tangent-ogive slender body,the PIV tests were carried through in high speeds wind tunnel to investigate the asymmetric vortex flow at high angles of attack.The Mach number ranged from 0.4 to 1.2,and angle of attack was fixed to 40°.The results showed that asymmetric multi-vortex flow structure still exist in high speed case, and both Reynolds number and compressibility affect asymmetric vortex flow phenomenon.It was observed that there was a distinct relation between tip perturbation and response of asymmetric vortex flow.

关 键 词：大迎角空气动力学 压缩性 非对称涡 细长体 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]