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发展翼身组合体复杂外形流动转捩自动判断方法,对高亚声速民机自然层流(NLF)机翼设计具有重要意义.使用多块结构化网格和三维雷诺平均Navier-Stokes(RANS)方程求解器,耦合边界层方程求解和基于线性稳定性理论(LST)的完全双eN方法,发展了一套可同时计及Tollmien-Schlichting波和横流不稳定性扰动诱导转捩的翼身组合体流动转捩自动判断方法.对DLR-F4翼身组合体绕流进行了转捩自动判断,将得到的转捩位置与试验结果进行比较,验证了所发展方法的正确性.使用上述方法对配置自然层流机翼的中短程民机翼身组合体外形进行了数值模拟,并将结果与单独机翼的转捩位置进行了对比,结果表明机身三维位移效应增强了自然层流后掠机翼边界层的横流不稳定性强度,导致翼根转捩位置提前至前缘区.“,”Development of the automatic transition prediction method for complex wing-body configurations is of great importance for the design of the Natural Laminar Flow (NLF) wing of high-subsonic civil transport aircraft.An automatic transition prediction method for wing-body configurations is developed using the structured multi-block grid three-dimensional ReynoldsAveraged Navier-Stokes (RANS) solver coupled with the fully dual eN method based on the Linear Stability Theory (LST).The method proposed can predict the transition induced by Tollmien-Schlichting instability and cross-flow instability simultaneously.Transition prediction of the flow around the DLR-F4 wing-body configuration is carried out,and a comparison of the transition locations given by the numerical method and by the experiment validates the accuracy of the proposed method.The flow around the wing-body configuration of short and medium range civil transport aircraft using the NLF wing is simulated,and the simulation results are compared with the transition locations of the individual wing.The comparison result shows that the cross-flow instability of the NLF aft-swept wing boundary layer is increased due to the three-dimensional displacement of the fuselage,leading to early transition onset in the leading edge region of the wing root.