北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (3): 470-479.doi: 10.13700/j.bh.1001-5965.2017.0216

• 论文 • 上一篇    下一篇

一种跨声速定常流场求解加速方法

乔磊1, 白俊强1, 邱亚松1, 华俊1,2, 张扬3   

  1. 1. 西北工业大学航空学院, 西安 710072;
    2. 中国航空工业集团有限公司中国航空研究院, 北京 100012;
    3. 西安交通大学航天航空学院, 西安 710049
  • 收稿日期:2017-04-10 出版日期:2018-03-20 发布日期:2018-03-30
  • 通讯作者: 邱亚松 E-mail:qiuyasong@nwpu.edu.cn
  • 作者简介:乔磊,男,博士研究生。主要研究方向:计算流体力学;白俊强,男,博士,教授,博士生导师。主要研究方向:飞行器设计、设计空气动力学、非定常空气动力学、工程湍流模拟。邱亚松,男,博士,助理工程师。主要研究方向:飞行器气动设计、计算流体力学与降阶方法;华俊,男,博士,教授,博士生导师。主要研究方向:飞行器气动设计、机翼防冰系统数值模拟、计算流体力学与控制系统耦合;张扬,男,博士研究生。主要研究方向:工程湍流模拟、流动控制。
  • 基金资助:
    国家自然科学基金(11502211,11602199)

High-efficiency solving method for steady transonic flow field

QIAO Lei1, BAI Junqiang1, QIU Yasong1, HUA Jun1,2, ZHANG Yang3   

  1. 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072;
    2. China Aeronautical Establishment, Aviation Industry Corporation of China, Ltd., Beijing 100012, China;
    3. School of Aerospace, Xi'an Jiaotong University, Xi'an 710049, China
  • Received:2017-04-10 Online:2018-03-20 Published:2018-03-30
  • Supported by:
    National Natural Science Foundation of China (11502211, 11602199)

摘要: 跨声速定常流场的隐式求解相当于使用牛顿迭代法求解一个非线性方程组。为满足牛顿迭代收敛性的要求,通常需要对所求解问题进行全局化处理。在同伦延拓的框架内,提出了一种基于拉普拉斯算子的方程延拓方法,提高了定常流场隐式求解收敛速度。针对定常流场通常初始化为均匀来流的特点,一方面利用拉普拉斯算子的椭圆性加快边界条件信息向流场内部的传播,另一方面利用拉普拉斯算子的线性和正定性改善延拓问题的正则性,综合两者增加拟牛顿算法的稳定性,提高可用CFL数,最终达到提高流场求解效率的目的。由于流场问题的复杂性和非线性,难以通过理论分析得出先验的最优非线性求解策略。因此,通过无黏NACA0012翼型、湍流RAE2822翼型和三维ONERA M6机翼等算例的数值实验,研究了拉普拉斯项参数对收敛效率的影响,给出了效率较优的参数组合,验证了本文方法在跨声速情况下相对于经典伪时间推进法可以节约20%以上的CPU计算时间。

关键词: 非线性方程, 隐式格式, 牛顿法, 空气动力学, 跨声速, 定常流动

Abstract: The implicit solving approach of steady transonic flow field equals a Newton iteration for a nonlinear equation system. Globalization of Newton iteration is usually necessary in practice in order to fulfill the convergence requirement. In the framework of homogenous continuation, a Laplace operator based function continuation method which accelerates convergence of implicit solving of steady flow field is proposed. Considering that the steady flow field is usually initialized as uniform freestream condition, the Laplace operator is employed to speed up information propagation from wall boundary to internal flow field due to its ellipticity and to improve regularity of the problem due to its linearity and symmetric positive definite property. Thus the stability of Newton's method is improved then larger CFL number could be employed and finally the flow field solving efficiency is improved. Due to the complexity and nonlinearity of the flow field problem, a priori optimal nonlinear solving strategy is impossible to be obtained through theoretical analysis. Thus, the effect of Laplacian coefficient on convergence efficiency is investigated through numerical experiments on inviscid NACA0012 airfoil, turbulent RAE2822 airfoil and ONERA M6 3D wing test cases. Generally pragmatic combination of iteration parameters are also given and the proposed method is proved to gain over 20% saving in CPU computing time compared with the classic pseudo time marching method under transonic condition.

Key words: nonlinear equations, implicit scheme, Newton's method, aerodynamics, transonic, steady flow

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