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首页> 外文期刊>Canadian Aeronautics and Space Journal >The Application of a Number of Turbulence Models for Calculating 2-D and 3-D Navier Stokes Flows with Separation
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The Application of a Number of Turbulence Models for Calculating 2-D and 3-D Navier Stokes Flows with Separation

机译：多个湍流模型在分离计算二维和三维Navier Stokes流中的应用

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This paper investigates the performance of four turbulence models: Baldwin-Lomax, Johnson-King, Baldwin-Barth, and k-ε with Chien's near wall modification. The turbulence models were applied to 2-D and 3-D flows known to contain separation. For 2-D studies, airfoils RAE 2822 (cases 9 and 10), MBB-A3 airfoil at M=0.84, α=1.78° and Re=6.08 x 10~6, and NACA 4412 airfoil at M=0.0827, Re=1.52 x 10~6 for α's up to stall conditions were selected. For 3-D investigation, the ONERA M6 wing at α=3.06? and 5.05°, with M=0.84 and Re=11.7 x 10~6 was chosen. Results for the pressure distribution prediction indicate that for 2-D flows with separation, the one-equation Baldwin-Barth turbulence model performed as well as, if not better than, the higher-order k-ε turbulence model. The Baldwin-Lomax and Johnson-King turbulence models tended to overpre-dict the shock location. For the viscous calculations, parameters like skin-friction and displacement thicknesses compared well between the Baldwin-Barth and k-ε models; however, the velocity profiles obtained using the Baldwin-Barth model did not fare as well. For 3-D flows, again it was observed that the Baldwin-Barth turbulence model provided the closest match with experimental measurements both in terms of pressure levels and the shock location predictions. Contours of constant pressure lines and computed f lowfield particle traces for the higher angle of attack case show complex 3-D separation and flow reversal toward the tip of wing. This flow behaviour was found to be consistent with computed results reported in literature.
机译：本文研究了四种湍流模型的性能：Baldwin-Lomax，Johnson-King，Baldwin-Barth和带有Chien近壁修饰的k-ε。湍流模型应用于已知包含分离的2-D和3-D流。对于2-D研究，翼型为RAE 2822（案例9和10），M = 0.84，α= 1.78°和Re = 6.08 x 10〜6的MBB-A3翼型，M = 0.0827，Re = 1.52的NACA 4412翼型为α直至失速条件选择x 10〜6。为了进行3D研究，α= 3.06°的ONERA M6机翼？和5.05°，M = 0.84和Re = 11.7×10〜6。压力分布预测的结果表明，对于带有分离的二维流动，执行的是一方程式Baldwin-Barth湍流模型，如果不是更好的话，则表现得比高阶k-ε湍流模型好。 Baldwin-Lomax和Johnson-King湍流模型倾向于高估冲击位置。对于粘性计算，Baldwin-Barth模型和k-ε模型之间的参数如皮肤摩擦和位移厚度进行了比较。但是，使用Baldwin-Barth模型获得的速度分布也不理想。对于3-D流动，再次观察到，鲍德温-巴特湍流模型在压力水平和冲击位置预测方面都提供了与实验测量值最接近的匹配。对于较高攻角的情况，恒压线的轮廓和计算出的低场粒子迹线显示出复杂的3-D分离和流向机翼尖端的逆流。发现这种流动行为与文献报道的计算结果一致。

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