航空科学技术Issue(11)：23-29,7.
耦合转捩自动判断的机翼粘性绕流计算与优化设计
Simulations of the Viscous Flow around Swept Wings and Optimization Design Using the RANS Solver with Automatic Transition Prediction
摘要
Abstract
The Reynolds-Averaged Navier-Stokes (RANS) solver which can predict the boundary layer transition is a necessary means for the drag reduction design and the natural laminar lfow wing design. A dual N factor (NTS/NCF) transition prediction method based on the linear stability theory was coupled to the three-dimensional RANS solver to improve the accuracy of the solver. By solving the three dimensional linear stability equations, the instabilityNTS which corresponds to the Tolmien-Schlichting was calculated based on the envelope strategy, and theNCF which corresponds to the crosslfow instability was gotten based on the ifxedβ strategy. Then, the transition position was predicted with the transitionN factors (NTS)tr and (NCF)tr being determined according to the experimental data. With the developed method, the drag minimization of a baseline natural laminar lfow (NLF) wing by changing the wing planform is studied.关键词
转捩判断/eN方法/RANS求解器/Kriging模型/优化Key words
transition prediction/eN method/RANS solver/Kriging model/optimization分类
航空航天引用本文复制引用
宋文萍,朱震,张坤,韩忠华..耦合转捩自动判断的机翼粘性绕流计算与优化设计[J].航空科学技术,2015,(11):23-29,7.基金项目
航空科学基金（1998ZA53002，2009ZA53008）@@@@Aeronautical Science Foundation of China （）
