基于高阶WENO格式的旋翼非定常涡流场数值模拟

doi:10.7527/S1000-6893.2015.0281

气动/运动耦合数值模拟研究

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基于高阶WENO格式的旋翼非定常涡流场数值模拟

印智昭, 招启军, 王博

南京航空航天大学直升机旋翼动力学国家级重点实验室, 南京 210016

收稿日期:2015-08-18 修回日期:2015-10-16 出版日期:2016-08-15 发布日期:2015-11-30
通讯作者: 招启军,Tel.:025-84893753。E-mail:zhaoqijun@nuaa.edu.cn E-mail:zhaoqijun@nuaa.edu.cn
作者简介:印智昭,男,硕士研究生。主要研究方向:直升机计算流体力学、高精度CFD数值格式。E-mail:yinzhizhao@nuaa.edu.cn;招启军,男,博士,教授,博士生导师。主要研究方向:直升机计算流体力学、直升机空气动力学及流动控制、气动噪声、总体设计。Tel:025-84893753。E-mail:zhaoqijun@nuaa.edu.cn;王博,男,博士,讲师。主要研究方向:直升机计算流体力学、直升机空气动力学、新概念旋翼飞行器气动设计等。Tel:025-84893753。E-mail:wangbo@nuaa.edu.cn
基金资助:
国家自然科学基金（11272150）；江苏高校优势学科建设工程基金

Numerical simulations for unsteady vortex flowfield of rotors based on high-order WENO scheme

YIN Zhizhao, ZHAO Qijun, WANG Bo

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2015-08-18 Revised:2015-10-16 Online:2016-08-15 Published:2015-11-30
Supported by:
National Natural Science Foundation of China (11272150);Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要：

为提高直升机旋翼黏性涡流场计算流体力学（CFD）的计算精度及降低数值耗散，发展了一套基于五阶加权本质无振荡（WENO）格式的旋翼非定常涡流场数值计算方法。采用运动嵌套网格方法生成围绕前飞状态旋翼的网格系统，以Navier-Stokes方程作为主控方程，湍流模型采用一方程Spalart-Allmaras模型。为了提高旋翼流场中对涡的形成、演化等发展过程的模拟精度，采用高间断分辨率的Roe-WENO格式计算对流通量。对状态变量的插值，选取适当的加权因子，通过多个重构模板的凸组合来构造五阶WENO格式，在交界面附近获得具有五阶精度的状态变量。为了提高计算效率，采用高效的隐式LU-SGS（Lower-Upper Symmetric Gauss-Seidel）推进方法和并行计算策略。最后，运用该方法分别对悬停状态下C-T（Caradonna-Tung）旋翼和UH-60A旋翼以及前飞状态下C-T旋翼和SA349/2旋翼的涡流场及气动特性进行了数值模拟，并将数值结果与传统二阶精度格式的计算值进行了对比。结果表明：在计算时间增长10%～20%的前提下，五阶WENO格式能够捕捉到更精确的涡流场特性，反映了五阶WENO格式在计算旋翼非定常涡流场时具有更高的计算精度与更低的数值耗散特性。

关键词: 旋翼, 涡流, 加权本质无振荡格式, Navier-Stokes方程, 桨尖涡, 运动嵌套网格

Abstract:

Aimed at improving the computational fluid dynamics (CFD) computation accuracy and reducing the numerical dissipation of the vortex flowfield of helicopter rotor, the highly-accurate CFD method based on fifth-order weighted essentially non-oscillatory (WENO) scheme has been established for numerical simulation on the unsteady flowfield of rotors. In this method, the moving-embedded grid technique has been employed in the numerical simulation, the Navier-Stokes equations have been taken as governing equations, and one equation Spalart-Allmaras turbulence model has been employed. In order to improve the computation accuracy of the rotor vortex formation and evolution, the discretization of convective fluxes and the time marching are conducted by Roe-WENO scheme and the highly efficient implicit LU-SGS (Lower-Upper Symmetric Gauss-Seidel) scheme respectively, and the parallel strategy is employed to accelerate the calculation as well. The computation of the left and right flow quantities is based on the fifth-order WENO scheme, which uses the appropriate weights to combine all the candidate stencils to obtain the fifth-order approximation. Finally aerodynamic characteristics and blade-tip vortex of the several rotors (C-T and UH-60A rotor in hover, C-T rotor in non-lifting forward flight and SA349/2 rotor in forward flight) have been simulated by the present method. Comparing numerical results with experimental data and calculated results using the JST scheme and Roe-MUSCL scheme, it is demonstrated that the present method with only 10%~20% increase of computational consumption has high accuracy and low numerical dissipation in simulating the aerodynamic characteristics and blade-tip vortex.

Key words: rotor, vortex flow, weighted essentially non-oscillatory scheme, Navier-Stokes equations, blade-tip vortex, moving-embedded grid

中图分类号:

印智昭, 招启军, 王博. 基于高阶WENO格式的旋翼非定常涡流场数值模拟[J]. 航空学报, 2016, 37(8): 2552-2564.

YIN Zhizhao, ZHAO Qijun, WANG Bo. Numerical simulations for unsteady vortex flowfield of rotors based on high-order WENO scheme[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(8): 2552-2564.

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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

基于高阶WENO格式的旋翼非定常涡流场数值模拟

Numerical simulations for unsteady vortex flowfield of rotors based on high-order WENO scheme

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