Langtry-Menter转捩模型的高超声速修正与验证  

Hypersonic modification and verification of Langtry-Menter transition model

作　　者：李城锐 江中正 吴昌聚[1] 杨雨欣 邓思超 LI Chengrui;JIANG Zhongzheng;WU Changju;YANG Yuxin;DENG Sichao(School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,China;Research and Development Department,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]浙江大学航空航天学院,杭州310027 [2]中国运载火箭技术研究院研究发展部,北京100076

出　　处：《航空动力学报》2024年第11期343-352,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(U20B2007)。

摘　　要：针对高超声速边界层转捩流动预测问题,基于传统Langtry-Menter转捩模型和SST(shear stress transport)湍流模型开展高速修正方法研究,将高超声速横流判据修正、湍动能压力膨胀项可压缩性修正和压力梯度系数修正引入到原始转捩模型,以拓展模型在高超声速边界层流动转捩的预测能力,并采用超声速平板、0°攻角高超声速直锥、小攻角高超声速尖锥和HIFiRE-5等6个典型算例对修正后的转捩模型的预测能力进行验证。研究结果表明:修正后的转捩模型所预测的转捩起始位置、转捩终点位置和转捩区长度与实验结果基本吻合,壁面摩擦阻力和热流的计算结果与实验测量结果基本一致,修正后的转捩模型对高超声速边界层转捩的预测能力较好。For the prediction of hypersonic boundary layer transition flow,three types of high-speed modified methods were studied based on the traditional Langtry-Menter transition model and SST(shear stress transport)turbulence model.The modification of hypersonic cross-flow criterion,compressibility modification of turbulent kinetic energy pressure dilatation term and modification of pressure gradient coefficient were introduced into the original transition model to expand the simulation capacity of the model in hypersonic flow.The modified transition model was validated by using several typical cases:supersonic plate,hypersonic cone with zero angle of attack,hypersonic cone with small angle of attack and hypersonic HIFiRE-5.The results showed that the predicted transition-start position,transition-end position and transition zone length of the modified model were basically consistent with the experimental results.The calculated results of skin friction and heat flux were basically consistent with the experimental measurement data.The modified transition model performed well in predicting hypersonic transition flow.

关 键 词：高超声速流动 边界层 横流判据 流动转捩 湍流模型 

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]