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.
出处
《飞行力学》
CSCD
北大核心
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)
关键词
风洞实验
飞行器
大迎角
非对称涡
wind tunnel experiment
air vehicle
high angle of attack
asymmetric vortex
