Towards Three-Dimensional Global Stability Analysis of Transonic Shock Buffet
Towards Three-Dimensional Global Stability Analysis of Transonic Shock Buffet
复制标题
跨音速激波冲击的三维全局稳定性分析
DOI：
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发表时间：
2016
期刊：
影响因子：
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通讯作者：
R. Thormann
中科院分区：
文献类型：
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作者：
S. Timme;R. Thormann
版权所有(C#2016)，作者：S.Timme和R.Thormann。本文对具有代表性的大型民用飞机半翼身布局的绕流问题进行了数值研究。特别是，我们感兴趣的是预测激波抖振不稳定性的开始。考虑了采用单方程Spalart-Allmaras湍流模型的雷诺平均Navier-Stokes模拟。首先，进行强迫运动时间线性化分析，以研究在接近抖振起始攻角时气动系数的频率响应特性。其次，对这种实际布局的飞机在具有强激波和边界层分离的跨音速湍流中进行了三个非均匀空间方向的全局稳定性分析。采用隐式重启Arnoldi方法，结合先进的稀疏迭代线性方程求解器和工业计算流体动力学程序包，在激波抖振开始附近的流动条件下，计算了靠近复杂平面原点的完整流体雅可比矩阵的几个特征值。
Copyright © 2016 by S. Timme and R. Thormann. Published by the American Institute of Aeronautics and Astronautics, Inc. A numerical study of the flow over a half wing-body configuration representative of a large civil aircraft is presented. In particular, we are interested in predicting the onset of the shock buffet instability. Reynolds-averaged Navier-Stokes simulations using the one- equation Spalart-Allmaras turbulence model are considered. First, forced-motion, time- linearised analysis is performed to investigate the frequency response behaviour of aero- dynamic coefficients while approaching the buffet onset angle of attack. Secondly, global stability analysis with three inhomogeneous spatial directions is achieved for this realistic aircraft configuration in transonic turbulent flow with strong shock waves and boundary layer separation. The implicitly restarted Arnoldi method is applied, in conjunction with an advanced sparse iterative linear equation solver and an industrial computational fluids dynamics package, to calculate few eigenvalues of the complete fluid Jacobian matrix close to the origin of the complex plane for flow conditions near shock buffet onset.