基于PSP/PIV技术的小展弦比飞翼跨声速横向失稳流动机理研究  

Study on Transonic Transverse Instability Flow Mechanism of Small Aspect Ratio Flying Wings Based on PSP/PIV Technology

作　　者：李欣昂 张杰 李玉军[1] 张雪[1] 才义 潘金柱[1] Li Xin’ang;Zhang Jie;Li Yujun;Zhang Xue;Cai Yi;Pan Jinzhu(Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Numbers Aerodynamic Force Research,AVIC Aerodynamic Research Institute,Shenyang 110034,China)

机构地区：[1]中国航空工业空气动力研究院高速高雷诺气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《气动研究与试验》2024年第6期79-84,共6页Aerodynamic Research & Experiment

摘　　要：小展弦比飞翼布局采用大后掠三角翼外形,在跨声速状态下易出现横向失稳运动,为了研究其发生机理及发展过程,本文综合采用压敏涂层测压/粒子图像测速(PSP/PIV)流场显示技术并结合自由滚转试验,获取了模型表面及空间尾流变化过程,成功捕捉到小展弦比飞翼标模出现横向失稳条件下左右机翼表面流场及空间尾流的非对称现象。研究结果表明,小迎角下,模型表面及空间尾流的压力分布并未出现很明显的非对称性,迎角增大以后,模型表面附着涡破裂并发生非对称分离,造成左右机翼压力存在高频及且幅值不等的振荡,导致了机翼摇滚运动的发生。The aircraft with low aspect ratio flying wing layout adopts the shape of large swept delta wing,which is prone to transverse instability movement in transonic state.In order to study its occurrence mechanism and development process,this paper comprehensively adopts PSP/PIV flow field visualization techniques and combines with free-to-roll test to obtain the change process of model surface and space wake.The asymmetrical phenomena of the left and right wing surface flow field and space wake are captured successfully under the condition of transverse instability of the wing model with low aspect ratio.The results show that there is no obvious asymmetry in the pressure distribution of the model surface and the space wake at a low angle of attack.When the angle of attack increases,the attached vortices on the model surface break up and asymmetrically separate,resulting in high frequency and unequal amplitude oscillations of the pressure on the left and right wings,and leading to the occurrence of wing rock motion.

关 键 词：PSP PIV 小展弦比飞翼 横向失稳 自由滚转 

分 类 号：V212.12[航空宇航科学与技术—航空宇航推进理论与工程]