Buffeting in transonic flow prediction using time‐dependent turbulence model
Buffeting in transonic flow prediction using time‐dependent turbulence model
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DOI：
10.1002/fld.991
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发表时间：
2005-09
影响因子：
1.8
通讯作者：
A. Kourta;G. Petit;J. Courty;J. Rosenblum
中科院分区：
文献类型：
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作者：
A. Kourta;G. Petit;J. Courty;J. Rosenblum
在跨音速流动条件下，激波/湍流边界层的相互作用和机翼上表面的流动分离导致流动不稳定，即“抖振”，进而产生抖振(结构振动)。这种现象会对气动性能产生很大的影响。这些流动激励是自我维持的，并由于压力波动而导致表面作用力。它们可以产生足够的能量来刺激结构。本文的目的是利用非定常N-S方程和基于合适的(k-ε)湍流涡粘性模型的含时湍流模型来准确地预报这一非定常现象。所用模型基于湍流粘性概念，其中湍流粘性系数(Cμ)与局部变形和旋转速度有关。为了验证该模型的有效性，首先计算了马赫数为0.6的平板绕流，然后计算了NACA0012翼型的绕流。与分析结果和实验结果进行了比较，结果吻合较好。选择ONERA OAT15A跨音速翼型来描述抖振现象。采用流线迎风Petrov-Galerkin(Stream Up Wind Petrov-Galerkin)有限元求解器进行数值模拟。计算结果表明，该模型具有较强的预测水流振荡物理现象的能力。描述了非定常激波与边界层的相互作用。版权所有©2005 John Wiley&Sons，Ltd.
In transonic flow conditions, the shock wave/turbulent boundary layer interaction and flow separations on wing upper surface induce flow instabilities, ‘buffet’, and then the buffeting (structure vibrations). This phenomenon can greatly influence the aerodynamic performance. These flow excitations are self‐sustained and lead to a surface effort due to pressure fluctuations. They can produce enough energy to excite the structure. The objective of the present work is to predict this unsteady phenomenon correctly by using unsteady Navier–Stokes‐averaged equations with a time‐dependent turbulence model based on the suitable (k–ε) turbulent eddy viscosity model. The model used is based on the turbulent viscosity concept where the turbulent viscosity coefficient (Cμ) is related to local deformation and rotation rates. To validate this model, flow over a flat plate at Mach number of 0.6 is first computed, then the flow around a NACA0012 airfoil. The comparison with the analytical and experimental results shows a good agreement. The ONERA OAT15A transonic airfoil was chosen to describe buffeting phenomena. Numerical simulations are done by using a Navier–Stokes SUPG (streamline upwind Petrov–Galerkin) finite‐element solver. Computational results show the ability of the present model to predict physical phenomena of the flow oscillations. The unsteady shock wave/boundary layer interaction is described. Copyright © 2005 John Wiley & Sons, Ltd.