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边界层转捩位置的准确预测对于提高飞行器气动性能的预测精度具有重要意义。选取与k-ωSST湍流模型相耦合的γ-Reθt模型,以零压力梯度平板为研究对象,通过求解基于有限体积法的雷诺平均N-S方程验证该模型自动捕捉流动转捩的准确性;将该模型应用于传统有压力梯度的NACA 0012翼型的流场特性和气动性能的研究中,并与原始k-ωSST模型的计算结果及全湍流试验数据进行比较。结果表明:远场边界距离对翼型阻力系数有较大的影响;与无转捩模型相比,γ-Reθt转捩模型对翼型阻力系数的预测精度有一定程度的提高;对于二维模型,γ-Reθt转捩模型难以捕捉翼型表面的三维效应和非定常分离特性。
The accurate prediction of the boundary layer transition is of great significance to improve the prediction precision of aerodynamic performance of aircraft. The γ-Reθt model coupled with the k-ωSST turbulence model is selected and the zero-pressure gradient plate is taken as the research object. The accuracy of the model is verified automatically by solving the Reynolds-averaged Navier-Stokes equations for Navier-Stokes equations. It is applied to the study of the flow field and aerodynamic performance of the conventional NACA 0012 airfoil with pressure gradient and compared with the results of the original k-ωSST model and the data of the full turbulence test. The results show that the far-field boundary distance has a great influence on the airfoil drag coefficient. Compared with the no-twist model, the γ-Reθt transition model improves the prediction accuracy of the airfoil drag coefficient to some extent. For the two-dimensional model , γ-Reθt transition model is difficult to capture three-dimensional airfoil surface effects and unsteady separation characteristics.