转捩模型在翼型气动性能预测中的应用研究  

Research on Application of Transition Model in Prediction of Airfoil Aerodynamic Characteristics

作　　者：张瑞民[1] 时晓天[1] 

机构地区：[1]中国航天空气动力技术研究院第二研究所,北京100074

出　　处：《航空工程进展》2016年第4期426-432,共7页Advances in Aeronautical Science and Engineering

摘　　要：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。It is of important significance for improving the prediction accuracy of aircraft aerodynamic performance to predict the transition position of the boundary layer accurately. Selecting the γ-Reθt, model coupled with k-ω SST turbulence model and taking no-pressure-gradient plane as an example, the capability of this model for trapping flow transition automatically is verified. Then the model is applied to study the flow characteristics and aerodynamic performance of NACA 0012 airfoil with pressure gradient, the results from which are compared with the computational results from original k-ω SST model and the test data of complete turbulence model. The study shows that far-field boundary has a great impact on airfoil drag coefficient. Compared to no-transition model, γ-Reθt transition model is of some improvement on predicting airfoil drag coefficient. It is difficult for γ-Reθt transition model to simulate 3-d airflow field and separate characteristics of 2-d model.

关 键 词：转捩 湍流 翼型 平板 气动特性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]