改进的k-ω模型在亚音速漩涡流动中的应用

The Application of Enhanced k-ω Model in Simulation on Subsonic Vortex Flow

基于非结构网格,采用经典的wilcox k-ω模型和其改进的kω-Pω模型,建立了用于模拟大攻角旋涡流动的计算方法。以尖前缘的65°三角翼为例,模拟了旋涡的产生、发展、破裂过程,验证了wilcox k-ω模型和kω-Pω模型在典型的亚音速计算状态下对复杂涡系干扰的模拟能力。通过对多种计算的流场与气动力详细结果的比较分析,就两种湍流模型对大攻角复杂旋涡流动的预测能力和敏感性等进行了评估。结果表明:kω-Pω模型通过r值区分剪切层和涡核区域,从而对涡核区域的涡黏性进行修正。对最后的模拟结果有一定的修正作用,可以作为湍流模型修正的一个方向。RANS方法在预测涡破裂点位置和二次涡的强度及位置方面仍存在很大的缺陷。

A numerical simulation method on the flow characteristics over delta wing at high angle of attack based on unstructured grids with wilcox k-ω and k-ω with Pω enhancer turbulence model is investigated.To analyze the applicability of wilcox k-ω and k-ω with Pω enhancer turbulence models on simulating the vortex flow,a sharp leading edge delta wing with a leading edge sweep of 65° is applied to investigate the generation,developing and breakdown of vortex.The comparison for results obtained using wilcox k-ω model and k-ω with Pω enhancer model shows that the enhanced model controls the eddy viscosity within the regions of highly ratational flow.