风洞洞壁干扰数值模拟研究  

Numerical Simulation of Wind Tunnel Wall Interference

作　　者：杨依峰 王锁柱 董超[1] 杨天鹏 苏伟[1] Yang Yi-feng;Wang Suo-zhu;Dong Chao;Yang Tian-peng;Su Wei(Beijing Institute of Space Long March Vehicle,Beijing,100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术》2021年第6期73-77,共5页Missiles and Space Vehicles

摘　　要：风洞实验在飞行器研制过程中起着非常重要的作用,但是风洞洞壁的存在对飞行器的气动特性产生了显著的干扰影响,有必要对洞壁干扰做相关研究。针对风洞实验的特点,发展基于“风洞洞壁静压监测反馈调节系统”的数值模拟方法,通过该调节系统使风洞的数值模拟状态达到风洞实验的目标状态,并利用该调节系统对后掠机翼的风洞实验进行数值模拟,将数值模拟结果与实验数据进行对比,对比结果验证了该反馈调节系统的可行性及数值方法的可靠性。此外,利用嵌套网格技术对不同攻角的后掠机翼风洞实验进行数值模拟,并将计算结果与自由来流状态下的计算结果进行对比,研究并分析了风洞洞壁对亚声速及跨声速风洞实验的干扰影响。结果表明,在亚声速情况下,风洞洞壁对流场的影响较小,而对于跨声速流动,洞壁干扰影响较强,激波位置向后移动,且移动幅度较大。Wind tunnel experiment plays a very important role in the process of the aircraft development,but the presence of wind tunnel wall has significant interference effects on the aerodynamic characteristics of the aircraft.Therefore it is necessary to do relevant research on wall interference.Considering the feature of wind tunnel experiment,a numerical simulation method based on a feedback control system of monitoring static pressure on wind tunnel wall has been developed.By using this system,the numerical condition of wind tunnel can be the same as the actual experimental condition.With the feedback control system,a wind tunnel test of the swept wing is simulated and the numerical results are compared with experimental data to verify the feasibility of the feedback regulation system and the reliability of this numerical method.Besides,a series of wind tunnel tests of the swept wing at different angle of attacks are simulated by using chimera grid and the calculated results are compared with that in free air to analyze the wall interference effects on the subsonic and transonic wind tunnel experiment.The results show that under subsonic condition,the wind tunnel wall interference effects on flow field are small,but for transonic flow,the wind tunnel wall interference effects are stronger and the shock position moves backward considerably.

关 键 词：数值模拟 风洞洞壁干扰 嵌套网格 

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]