横流不稳定性转捩预测模型

doi:10.7527/S1000-6893.2015.0062

流体力学与飞行力学

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横流不稳定性转捩预测模型

徐家宽¹, 白俊强¹, 乔磊¹, 黄江涛², 史亚云¹

1. 西北工业大学航空学院, 西安 710072;
2. 中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

收稿日期:2014-07-29 修回日期:2014-10-13 出版日期:2015-06-15 发布日期:2015-03-04
通讯作者: 白俊强 Tel.: 029-88492694 E-mail: junqiang@nwpu.edu.cn E-mail:junqiang@nwpu.edu.cn
作者简介:徐家宽男, 博士研究生。主要研究方向: 飞行器气动设计, 计算流体力学。 Tel: 029-88492694 E-mail: xujiakuanbond@163.com;白俊强男, 博士, 教授, 博士生导师。主要研究方向: 飞行器总体设计, 飞行力学, 计算流体力学。 Tel: 029-88492694 E-mail: junqiang@nwpu.edu.cn;乔磊男, 博士研究生。主要研究方向: 飞行器气动设计, 计算流体力学。 E-mail: qiaol618@163.com;黄江涛男, 博士。主要研究方向: 飞行器总体及气动设计, 气动弹性力学, 计算流体力学。 E-mail: hjtcfy@163.com;史亚云女, 硕士研究生。主要研究方向: 飞行器气动设计, 计算流体力学。 E-mail: 775042445@qq.com
基金资助:
国家"973"计划 (2014CB744804)

Transition model for predicting crossflow instabilities

XU Jiakuan¹, BAI Junqiang¹, QIAO Lei¹, HUANG Jiangtao², SHI Yayun¹

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2014-07-29 Revised:2014-10-13 Online:2015-06-15 Published:2015-03-04
Supported by:
National Basic Research Program of China (2014CB744804)

摘要/Abstract

摘要：

由于Langtry和Menter提出的γ-Re_θt边界层转捩模型只能预测流向的边界层转捩现象,因此继续改进该转捩模型使其具有横流不稳定性转捩的预测能力显得非常必要。通过对经典Falkner-Skan-Cooke (FSC)三维边界层相似解的理论分析和数值求解,结合Thwaites压力梯度因子与当地后掠角构建的函数关系来求解复杂构型的当地Hartree压力梯度因子β_H以及形状因子H₁₂,采用由试验数据标定的C1准则关系式获得横流转捩位移厚度雷诺数,从而建立能够对复杂构型进行横流不稳定性转捩预测的转捩判据。应用所建模型对30°前缘后掠角的ONERA-M6机翼和变前缘后掠角的DLR-F5机翼以及标准6:1椭球标模进行了横流不稳定转捩数值模拟,计算结果显示转捩位置均与试验数据吻合较好,证明了该模型的合理性和实用性。

关键词: 转捩模型, 横流不稳定性, 边界层相似解, Falkner-Skan-Cooke方程, 边界层, 雷诺数

Abstract:

As the γ-Re_θt boundary layer transition model proposed by Langtry and Menter could only predict the transition along the streamwise, it is necessary to develop a γ-Re_θt transition model so that it could conduct the numerical simulation of crossflow instabilities transition. With the theoretical analysis and numerical solution of Falkner-Skan-Cooke (FSC) three-dimensional boundary layer, combining the Thwaites pressure gradient factor with local swept angle to build the relationships for solving the Hartree pressure gradient factor β_H and the shape factor H₁₂, using the C1 criterion calibrated by the test data to get the crossflow instabilities transition displacement thickness Reynolds number, the crossflow transition criterion is established for complex configuration by solving the equations and data fitting. The model has been applied to conducting the numerical simulation of crossflow instabilities transition on the ONERA-M6 wing with 30° swept angle of leading edge, the DLR-F5 wing with variational swept angle of leading edge and the 6:1 prolate spheroids standard model. The numerical results show that the improved transition model could predict the location of crossflow instabilities transition of swept wing in good agreement with the test data. Therefore, the results indicate that the crossflow instabilities transition criterion built is reasonable and practical.

Key words: transition model, crossflow instabilities, boundary layer similar solution, Falkner-Skan-Cooke equation, boundary layers, Reynolds number

中图分类号:

V221

徐家宽, 白俊强, 乔磊, 黄江涛, 史亚云. 横流不稳定性转捩预测模型[J]. 航空学报, 2015, 36(6): 1814-1822.

XU Jiakuan, BAI Junqiang, QIAO Lei, HUANG Jiangtao, SHI Yayun. Transition model for predicting crossflow instabilities[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1814-1822.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

横流不稳定性转捩预测模型

Transition model for predicting crossflow instabilities

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