基于RANS-LES混合方法的翼型大迎角非定常分离流动研究

doi:10.7527/S1000-6893.2013.0263

流体力学与飞行力学

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基于RANS-LES混合方法的翼型大迎角非定常分离流动研究

刘周, 杨云军, 周伟江, 龚安龙

中国航天空气动力技术研究院, 北京 100074

收稿日期:2013-03-18 修回日期:2013-05-17 出版日期:2014-02-25 发布日期:2013-06-28
通讯作者: 刘周，Tel.：010-68743745 E-mail：zhou_liu@foxmail.com E-mail:zhou_liu@foxmail.com
作者简介:刘周男，硕士，高级工程师。主要研究方向：计算流体力学、飞行器气动外形设计。Tel：010-68743745 E-mail：zhou_liu@foxmail.com；杨云军男，博士，研究员。主要研究方向：飞行器动态特性、计算流体力学。Tel：010-68374026 E-mail：yangyj1998@163.com
基金资助:
国家自然科学基金（90916001）

Study of Unsteady Separation Flow Around Airfoil at High Angle of Attack Using Hybrid RANS-LES Method

LIU Zhou, YANG Yunjun, ZHOU Weijiang, GONG Anlong

China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received:2013-03-18 Revised:2013-05-17 Online:2014-02-25 Published:2013-06-28
Supported by:
National Natural Science Foundation of China (90916001)

摘要/Abstract

摘要：

使用雷诺平均Navier-Stokes方程-大涡模拟（RANS-LES）混合方法中的延迟分离涡模拟（DDES）方法，模拟了NACA 0015翼型在大迎角下的静态绕流和强迫振荡运动并与实验值进行了比较。在大迎角静态翼型大分离流动模拟中，DDES方法捕获了非定常RANS计算未能获得的机翼背风面的涡脱落现象。在所采用的RANS和DDES模型中，基于剪切应力输运（SST）湍流模型的SST-DDES混合方法给出的时均压力系数分布与实验吻合得最好。在大迎角强迫振荡翼型绕流模拟中，DDES方法得到的非定常气动载荷与实验值吻合得很好，正确地反映了最大迎角处阻力和俯仰力矩的阶跃性突变，而非定常RANS计算则给出了完全错误的趋势。

关键词: RANS-LES混合方法, 分离涡模拟, 流动分离, 涡脱落, 强迫振荡, 气动载荷, 大迎角

Abstract:

A delayed detached eddy simulation (DDES) method, which is a hybrid Reynolds average Navier-Stokes-large eddy simulation (RANS-LES) method, is proposed for static and oscillating NACA 0015 airfoil flow simulations and the computational results are compared with experiment data. The vortex shedding phenomenon of the massive separation flow on the leeward of the airfoil at high angles of attack is captured by the DDES method in static simulations, while it is ignored in unsteady RANS computations. The time averaged pressure coefficients given by the SST-DDES method which is based on the original shear stress transport (SST) turbulence model agree very well with experiment data in all proposed RANS and DDES models. The unsteady aerodynamic loads hysteresis curves obtained by the DDES method in forced oscillation airfoil flow computation at high angles of attack agree with the experiment data better than the traditional unsteady RANS simulation results do, and the step jump of the drag and pitch moment coefficients at the maximum angle of attack is described accurately, while the RANS method gives the absolutely wrong trend.

Key words: hybrid RANS-LES method, detached eddy simulation, flow separation, vortex shedding, forced oscillation, aerodynamic load, high angle of attack

中图分类号:

V211.3

刘周, 杨云军, 周伟江, 龚安龙. 基于RANS-LES混合方法的翼型大迎角非定常分离流动研究[J]. 航空学报, 2014, 35(2): 372-380.

LIU Zhou, YANG Yunjun, ZHOU Weijiang, GONG Anlong. Study of Unsteady Separation Flow Around Airfoil at High Angle of Attack Using Hybrid RANS-LES Method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(2): 372-380.

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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

基于RANS-LES混合方法的翼型大迎角非定常分离流动研究

Study of Unsteady Separation Flow Around Airfoil at High Angle of Attack Using Hybrid RANS-LES Method

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