In the present study, a hybrid RANS/LES model and a correlation-based transition model were coupled for simulating flow involving massive flow separation and laminar-turbulent transition including crossflow direction. For this purpose, blending of IDDES model and the $\gamma -{\text{Re}}_{\theta t}-C{F}^{+}$ transition model was accomplished in a tightly coupled manner. For validations, numerical simulations around a circular cylinder involving laminar flow separation without turbulent reattachment were conducted. Numerical simulations were also conducted for flows around an Aerospatiale A-airfoil at a larger Reynolds number accompanying turbulent flow reattachment. As an application of the present blended model for flows involving crossflow transition, calculations were performed for flows around a 6:1 prolate spheroid, and the results were compared with experiment and those without considering flow transition induced by the crossflow instability. Additional application was also made for flows around an ONERA M6 wing at a relatively high angle of attack, and the results were compared with those of the baseline models and experiment. It was founded that the results by the present blended model are in good agreements with experiment, and show improvements over other models by considering flow transition and unsteady flow feature simultaneously. It was concluded that the present blended model is useful for predicting flows involving massive flow separation and crossflow transition.

在本研究中，混合的RANS / LES模型和基于相关的过渡模型耦合在一起，以模拟涉及大规模流分离和层流-湍流过渡（包括横流方向）的流动。为此，将IDDES模型与$\gamma -{\text{关于}}_{\theta Ť}-C{F}^{+}$过渡模型以紧密耦合的方式完成。为了进行验证，在不进行湍流重新附着的情况下，进行了围绕层流分离的圆柱体周围的数值模拟。还对伴随湍流重新附着的较大雷诺数下的航空航天A型机翼周围的流动进行了数值模拟。作为本混合模型在涉及横流过渡的流动中的应用，对6：1扁长球体周围的流动进行了计算，并将结果与​​实验进行了比较，并且未考虑横流不稳定性引起的流动过渡。还以较高的迎角对ONERA M6机翼周围的气流进行了额外的应用，并将结果与​​基准模型和实验的结果进行了比较。结果表明，目前的混合模型的结果与实验结果吻合良好，并且通过同时考虑流动过渡和非稳态流动特征显示出对其他模型的改进。结论是，本混合模型可用于预测涉及大量流分离和错流过渡的流量。