压缩拐角激波/边界层干扰的可压缩湍流模型研究

推进技术 ›› 2017, Vol. 38 ›› Issue (2): 281-288.

压缩拐角激波/边界层干扰的可压缩湍流模型研究

宋友富¹,徐晶磊¹,张扬²,白俊强²,李蒙¹

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191,北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191,西北工业大学航空学院，陕西西安 710072,西北工业大学航空学院，陕西西安 710072,北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191

发布日期:2021-08-15
作者简介:宋友富，男，硕士生，研究领域为计算流体力学，湍流模式。
基金资助:
航空发动机气动热力国家级重点实验室基金(9140C410505150C41002)。

Research of Compressible Turbulence Model in Shock Wave/Boundary-Layer Interaction Flow at a Compression Corner

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China,School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China,School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China and National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究压缩拐角激波/边界层干扰问题，抓住可压缩流动中的密度变化特性，利用构造的可压缩Von Karman尺度，基于KDO(Kinetic Dependent Only)湍流模型，发展出可压缩湍流模型CKDO(Compressible Kinetic Dependent Only)。通过对8°，16°，20°和24°压缩拐角算例的数值模拟，测试了其对可压缩、激波/边界层干扰这一湍流难题的求解能力。计算结果表明，总体上CKDO模型对壁面压力和壁面摩擦阻力系数的捕捉能力优于其它模型，并且随着压缩拐角角度的增大，其描述该流动的能力更加突出。CKDO模型在24°压缩拐角处计算的分离区大小仅比实验大10%左右，明显比其它模型结果好。这表明CKDO模型在模拟激波/边界层干扰这一类流动中有较好的适用性。

关键词: 超声速流动；压缩拐角；可压缩修正；激波/边界层干扰；湍流模型

Abstract: To study the problem of shockwave/boundary-layer interaction at a compression corner，variable density characteristics in compressible flow was taken into account. A new turbulence model CKD (Compressible Kinetic Dependent Only) was constructed by incorporating compressible Von Karman scale into KDO model(Kinetic Dependent Only). The shockwave/boundary-layer interaction was simulated by cases of 8°，16°，20° and 24° at a compression corner. The results show that，CKDO has advantages than others in capturing pressure and friction coefficient near the wall. With the angles of compression corner increase，the ability to describle the flow for CKDO become more prominent than others and continue to agree well with experiment. The size of separation zone for CKDO is only about 10% larger than experiment on 24° compression corner，obviously better than the other model results. It indicates that turbulence model CKDO has good performance in simulating the flows near the wall such as shockwave/boundary-layer interaction flow.

Key words: Supersonic flow；Compression corner；Compressibility correction；Shock wave/boundary layer interaction；Turbulence model

宋友富,徐晶磊,张扬,白俊强,李蒙. 压缩拐角激波/边界层干扰的可压缩湍流模型研究[J]. 推进技术, 2017, 38(2): 281-288.

SONG You-fu¹,XU Jing-lei¹,ZHANG Yang²,BAI Jun-qiang²,LI Meng¹. Research of Compressible Turbulence Model in Shock Wave/Boundary-Layer Interaction Flow at a Compression Corner[J]. Journal of Propulsion Technology, 2017, 38(2): 281-288.

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