压缩性对细长体涡流非对称发展的影响  

Effects of Compressibility on the Asymmetry Development of Vortex Flow around a Slender Body

作　　者：杨云军[1] 崔尔杰[1] 周伟江[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《航空学报》2004年第4期333-338,共6页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(10032060)资助项目

摘　　要：通过数值方法对大迎角细长体湍流流场的模拟,探讨压缩性对细长体非对称绕流发展的影响。结果表明细长体顶端的极小扰动诱发显著的非对称绕流,非对称的涡系结构沿轴向是逐步演化的;在亚临界横流马赫数区间,马赫数越高非对称越显著;在超临界横流马赫数区间,细长体两侧出现横流激波,非对称的发展被抑制,马赫数越高非对称越弱。Numerical simulation of turbulent flow around a slender body is conducted to explore the effect of compressibility on the asymmetric development of vortex flow. As a result, the asymmetric flow observed in experiment is simulated by the introduction of a minute bump placed near the body apex. The asymmetric vortex structure grows gradually along the symmetrical axis of the slender body. Flow asymmetry is more obvious with a higher subcritical crossflow Mach number, and it is suppressed with an increasing supercritical crossflow Mach number due to the appearance of the crossflow shock waves on both sides of a slender body.

关 键 词：大迎角空气动力学 非对称涡 数值模拟 压缩性 

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]