中等尺寸翼型风洞侧壁干扰的数值模拟研究  

Study on Side Wall Interference of Moderate-sized 2-D Wind Tunnel by Numerical Simulation

作　　者：牛嵩[1] 张正科[1] 高超[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,西安710072

出　　处：《科学技术与工程》2011年第5期1006-1011,共6页Science Technology and Engineering

摘　　要：采用有限体积法求解三维雷诺平均Navior-Stokes方程对中等尺寸翼型风洞侧壁的影响进行数值模拟。着重研究了不同马赫数及迎角下,使翼型中心对称面的流动状态与相同来流条件下的二维无干扰流动状态相吻合所需要的最小展弦比。结果表明,随着马赫数及迎角的增加,所需要的最小展弦比均有所增加。尤其是有激波存在时,需要比较大的展弦比,才能使激波位置与无干扰结果一致。The finite volume scheme has been used to solve the Navier-Stokes equations for simulating the flow field in a moderate-sized two-dimensional transonic wind tunnel test section for the investigation of the side wall effects on the two-dimensional experimental data.Particular attention has been paid to a minimum necessary aspect ratio which a straight wing must satisfy to achieve a two-dimensional flow at least in the mid-span symmetrical central plane under different Mach numbers and different angles of attack.The analysis of the computed results shows that the minimum aspect ratio increases in general as Mach number or the angle of attack increases.Especially,in high subsonic Mach number,a large aspect ratio is needed to make the shock wave in the same position as in the real 2-d interference-free flow.

关 键 词：翼型风洞 侧壁干扰 展弦比 数值模拟 

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]