翼型与风洞侧壁交接角区分离流动研究  

THE STUDY ON SEPARATED JUNCTURE FLOW BETWEEN AIRFOIL AND WIND TUNNEL SIDE WALL

作　　者：焦予秦[1] 乔志德[1] 

机构地区：[1]西北工业大学翼型研究中心,西安710072

出　　处：《力学学报》2002年第5期785-789,共5页Chinese Journal of Theoretical and Applied Mechanics

摘　　要：运用Navier-Stokes数值模拟对翼型模型试验时风洞侧壁和翼型模型结合部拐角区黏型分离流动进行模拟,并将简单代数湍流模型扩展用于机翼/风洞侧壁拐角区流动.计算格式在空间上采用中心有限体积离散,在时间上采用多步Runge-Kutta时间步长格式进行积分.结果显示,在翼型模型风洞试验时,模型/侧壁拐角区、模型表面、侧壁表面和模型后形成复杂的黏性分离流动和二次分离,对实验结果产生很大的影响.By a numerical analytic method which simulates the viscous flow around the test model in wind tunnel by solving three-dimensional thin-layer Renolds-averaged Navier-Stokes equations, the separated flow in wing/wind-tunnel-side-wall juncture is investigated.. In the method, a cell-centered finite volume method in space and a five-step Runge-Kutta hybrid scheme as time matching method are adopted and Baldwin-Lomax turbulent model is extended to wing/wind-tunnel-side-wall juncture flow. The results show that in airfoil wind tunnel testing, there exist complicated separated flow in wing/wind-tunnel-side-wall juncture, the model surface, the side-wall surface and behind model, and it has influence on the testing results.

关 键 词：拐角区流动 NAVIER-STOKES方程 有限体积法 翼型模型 风洞实验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]