翼型与风洞侧壁交接角区分离流动研究

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.

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

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.