飞行器大迎角非对称涡与气动特性的实验研究  

Experimental Research on Asymmetric Vortices and Aerodynamic Characteristics of Aircraft at High Angle of Attack

作　　者：李峰[1] 叶正寅[1] 白存儒[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《飞行力学》2008年第3期78-81,共4页Flight Dynamics

基　　金：国家自然科学基金资助项目(10572120)

摘　　要：针对飞行器大迎角绕流的非对称气动特性,采用变湍流度技术,通过对细长体和翼身组合体模型的实验研究,分析了湍流度和人工扰动对飞行器大迎角流动非对称性的影响规律。实验结果表明,湍流度和人工扰动对飞行器大迎角情况下的非对称流动特性影响显著。The asymmetric aerodynamic characteristics of aircraft at high angle of attack are investigated. Adopting a converter turbulence technique and through the experimental study of slender cylinder and wing-body combination models, the effect of turbulence and manual micro perturbation on the asymmetric flow around them at high angle of attack is analysed. The obtained test results demonstrate the turbulence and manual micro perturbation can indeed affect the flow asymmetry occurring on the high-alpha aircraft models.

关 键 词：风洞实验 飞行器 大迎角 非对称涡 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]