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基于非结构网格,采用带曲率修正的显式代数应力非线性模型(EARSM)和微分雷诺应力模型(DRSM),建立了用于模拟大攻角旋涡流动的计算方法。分别以尖前缘和钝前缘的65°三角翼为例,验证了EARSM模型和DRSM模型在两种典型亚音速计算状态下对复杂涡系干扰的模拟能力和旋涡的产生、发展、破裂过程。分别利用SA、BSL两种线性湍流模型对相关问题进行了计算;通过对多种计算的流场与气动力详细结果的比较分析,就几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:EARSM和DRSM能较好地预测旋涡流动的发展破裂,强于经典线性湍流模型;对边界层发展状况预测较差,导致旋涡启动位置较早。基于算例计算,对两种先进湍流模型的改进提出了适当的建议。所得结论将可为进一步开展大攻角旋涡流动模拟方法的研究提供参考。
Based on the unstructured grid, an explicit algebraic stress nonlinear model with curvature correction (EARSM) and a differential Reynolds stress model (DRSM) are used to establish a method to simulate vortex flows at large angles of attack. Taking the 65 ° delta wing with sharp leading edge and blunt leading edge respectively as an example, the simulation capability of EARSM model and DRSM model for complex vortex system disturbances and the generation, development and rupture of vortices under two typical subsonic velocities are verified . Relevant problems are calculated by using two linear turbulence models, SA and BSL respectively. By comparing and analyzing the detailed results of the flow field and the aerodynamic force for various computations, the prediction ability of several turbulence models for complex swirling flow at large angle of attack and Sensitivity etc. were evaluated. The results show that EARSM and DRSM can better predict the rupture of vortex flow, which is stronger than the classical linear turbulence model. The prediction of the development of the boundary layer is poor, leading to the earlier vortex start. Based on the example calculation, some advices are put forward to improve the two advanced turbulence models. The conclusion will provide a reference for further research on the simulation of vortex flow at high attack angles.