基于放大因子与Spalart-Allmaras湍流模型的转捩预测

为了验证放大因子输运方程与Spalart-Allmaras(S-A)湍流模型耦合对转捩现象的模拟精度,选取Schubauer and Klebanoff(S-K)平板、S809低速翼型、30p30n多段翼型以及复杂的三维HiLiftPW-1构型进行自由转捩计算,并将计算结果与实验进行比较分析,其中针对S809算例,还与Langtry-Menter(L-M)转捩模型进行了比较.算例结果表明:放大因子输运方程与S-A湍流模型的耦合能够较好的捕捉转捩位置以及转捩发展过程,对分离泡诱导的转捩的模拟相比L-M转捩模型更精确,转捩位置的捕捉精度提升了10%;对比实验,多段翼转捩位置的捕捉误差最大为6.5%;针对三维高升力增升构型,以实验作为参考,全湍流计算与考虑边界层转捩的对比显示考虑边界层转捩能够更加精确的模拟气动力系数,升力和表面摩擦阻力系数的模拟精度精度提升1%.

Transition prediction based on amplification factorand Spalart-Allmaras turbulence model

To verify the simulation accuracy of current model coupling amplification factor transport equation with Spalart-Allmaras (S-A) turbulence model, Schubauer and Klebanoff flat plate (S-K), S809 low speed airfoil, 30p30n multi-element airfoil and complicated 3-D HiLiftPW-1 configure were selected for free transition calculation, and then, simulation results were compared with experimental results. Separately, current coupling model was compared with Langtry-Menter (L-M)transition model for S809 test cases. Test examples indicate that current coupling transition model can basically capture transition location and transition process, meanwhile, current coupling model performs better than L-M transition model in separated flow transition, and simulation accuracy increases by 10%; the maximum error of multi-element airfoil's transition position simulated is 6.5% compared with experiment data. For three dimensional high-lift configuration, comparison between full turbulence and free transition shows that considering boundary layer transition can simulate aerodynamic force coefficient more accurately and accuracy is promoted by 1%.