DLR-F6翼身组合体的高阶精度数值模拟

doi:10.7527/S1000-6893.2014.0362

流体力学与飞行力学

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DLR-F6翼身组合体的高阶精度数值模拟

王运涛¹, 孙岩², 王光学¹, 张玉伦¹, 李伟¹

1. 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;
2. 中国空气动力研究与发展中心空气动力学国家重点实验室, 绵阳 621000

收稿日期:2014-09-07 修回日期:2014-12-29 出版日期:2015-09-15 发布日期:2015-01-07
通讯作者: 王光学男, 博士研究生。主要研究方向: 计算空气动力学。 Tel: 0816-2463274 E-mail: gxwang@skla.cardc.cn E-mail:gxwang@skla.cardc.cn `
作者简介:王运涛男, 博士, 研究员, 博士生导师。主要研究方向: 计算空气动力学。 Tel: 0816-2463015 E-mail: ytwang@skla.cardc.cn;孙岩男, 博士研究生。主要研究方向: 计算流体力学。 Tel: 0816-2463205 E-mail: supersunyan@163.com;张玉伦男, 硕士, 副研究员。主要研究方向: 流体力学。 Tel: 0816-2463279 E-mail: ylzhang@skla.cardc.cn;李伟男, 硕士, 研究实习员。主要研究方向: 计算空气动力学。 Tel: 0816-2463274 E-mail: kuaileo6@163.com
基金资助:
国家重点基础研究发展计划 (2014CB744803)

High-order accuracy numerical simulation of DLR-F6 wing-body configuration

WANG Yuntao¹, SUN Yan², WANG Guangxue¹, ZHANG Yulun¹, LI Wei¹

1. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2014-09-07 Revised:2014-12-29 Online:2015-09-15 Published:2015-01-07
Supported by:
National Key Basic Research Program of China (2014CB744803)

摘要/Abstract

摘要：

基于雷诺平均Navier-Stokes(RANS)方程和结构网格技术,采用五阶空间离散精度的加权紧致非线性格式(WCNS)和剪切应力输运(SST)两方程湍流模型,开展了DLR-F6翼身组合体的高阶精度数值模拟研究。主要目的是确认WCNS模拟跨声速典型运输机构型的能力。采用粗、中、细3套网格开展了网格收敛性研究,从气动特性、压力分布、表面流态等方面研究了网格密度对DLR-F6翼身组合体气动特性的影响;采用中等网格开展了来流迎角对气动特性的影响研究。通过与试验数据、CFL3D软件和TRIP软件计算结果的对比,表明网格密度主要影响激波位置和压差阻力系数,同时对翼身结合部分离区大小有一定影响;采用高阶精度计算方法显著提高了气动力系数的模拟精度,力矩系数数值模拟结果与试验的差异有待进一步分析。

关键词: RANS方程, WCNS, 流场模拟, 网格密度, 气动特性

Abstract:

Based on the Reynolds-averaged Navier-Stokes (RANS) equations and structured grid technology, the fifth-order weighted compact nonlinear scheme (WCNS) and shear stress transport (SST) turbulence model are adopted to conduct a high-order numerical simulation of DLR-F6 wing-body configuration, for the purpose of validating the ability of WCNS in the simulation of typical transport configuration at transonic speed. The grid convergence study is performed with coarse, medium and fine grid systems, the effects of grid density on the simulation of DLR-F6 wing-body configuration are studied from aerodynamic characteristics, pressure distribution and flow pattern on the surface. The variation of aerodynamic characteristics with angles of attack is performed with the medium grid. Compared to the experimental data, CFL3D and TRIP results, the numerical results indicate that the grid density mainly affect the location of shock wave and pressure drag coefficient, and slightly affect the size of separation zone at the wing-body juncture. The numerical accuracy is significantly improved with high-order numerical method and the discrepancy of pitching moment coefficients between numerical data and experimental data needs further study.

Key words: RANS equations, weighted compact nonlinear scheme, flow simulation, grid density, aerodynamic characteristics

中图分类号:

V211.7

王运涛, 孙岩, 王光学, 张玉伦, 李伟. DLR-F6翼身组合体的高阶精度数值模拟[J]. 航空学报, 2015, 36(9): 2923-2929.

WANG Yuntao, SUN Yan, WANG Guangxue, ZHANG Yulun, LI Wei. High-order accuracy numerical simulation of DLR-F6 wing-body configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2923-2929.

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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

DLR-F6翼身组合体的高阶精度数值模拟

High-order accuracy numerical simulation of DLR-F6 wing-body configuration

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