翼身组合体摇滚特性高速试验研究  

Investigation on wing rock of wing-body configuration at high speed wind tunnel

作　　者：陶洋[1] 赵忠良[1] 杨海泳[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2011年第6期45-48,共4页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金项目(10972233)

摘　　要：简要介绍了翼身组合体高速风洞自由摇滚实验技术的实验装置、实验方法、数据采集等。开展了翼身组合体大迎角下的摇滚特性研究,给出了典型的结果,研究结果表明随着模型迎角的增加,翼身组合体呈现不同的滚转运动形态,包括静态稳定、准极限环摇滚等。所研究的参数范围内后掠角对摇滚有较大影响,随着模型迎角的增加摇滚振幅呈现抛物线,马赫数的增加对最大摇滚振幅起抑制作用。The free to roll test technique in high speed wind tunnel is presented in this paper, including test apparatus and test methods as well as data acquisition. A test investigation of the dynamic behavior of a wing-body configuration at high angle of attack was conducted. Dynamic motions were obtained on the wing-body configuration that was free to rotate about its longitudinal axis, different dynamic rolling motions were observed with the angle of attack of the model increasing. Two dynamic regimes included damped oscillations, quasi-limit-cycle rock motion. The sweep-back angle of the wing-body configuration have significant influence on the dynamic behavior in roll. The amplitude of the wing rock is parabolic with the angle of attack, and with the increase of Mach number the biggest wing rock amplitude are restrained.

关 键 词：摇滚 翼身组合体 大迎角 准极限环 高速风洞试验 

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]