基于修正边界层转捩的翼型气动特性研究  

Investigation of airfoil aerodynamic performance based on corrected boundary-layer transition

作　　者：张瑞民[1] 于金玲[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：《飞行力学》2013年第1期72-74,79,共4页Flight Dynamics

摘　　要：边界层转捩是决定翼型流场特性的重要因素,因此在航空工程中开展边界层转捩研究具有重要意义。从转捩流动的物理特征出发,引入间歇函数对k-ωSST两方程湍流模型的Wilcox转捩模式进行了修正,进而对传统的NACA0012翼型的流场特性和气动性能进行了研究,并与原始边界层转捩的计算结果以及试验结果进行了比较。研究表明,改进后的模型对转捩位置具有较好的预测能力;在采用修正边界层转捩模型的情况下,翼型的阻力预测精度有了一定程度的提高。Boundary layer transition is an important factor to determine the airfoil flow field characteris- tics. Therefore, it is of significance to study the boundary layer transition in aeronautical engineering. From the physical characteristics of the transition flow, the Wilcox transition mode in the k-to SST two- equation turbulence model was corrected with the introduction of the intermittent function. And thus the flow characteristics and aerodynamic performance of the traditional NACA0012 airfoil were studied and compared to the test results and to the results with original boundary layer transition. The results show that the transition position can be predicted by the modified model with certain accuracy and the predic- tion accuracy of airfoil drag characteristics has been improved to some extent by considering boundary lay- er transition.

关 键 词：边界层 转捩 翼型 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]