Transonic flutter computations for the NLR 7301 supercritical airfoil
Transonic flutter computations for the NLR 7301 supercritical airfoil
复制标题
NLR 7301 超临界翼型的跨音速颤振计算
DOI：
10.1016/s1270-9638(01)01099-9
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发表时间：
2001
影响因子：
5.6
通讯作者：
M. Platzer
中科院分区：
文献类型：
--
作者：
S. Weber;K. D. Jones;J. Ekaterinaris;M. Platzer
采用时域方法对NLR 7301剖面的跨音速稳态空气动力学和两自由度弯曲/扭转颤振特性进行了数值研究。一个非定常的，二维的，可压缩的，薄层的Navier-Stokes流动求解器耦合到一个两个自由度的结构模型。完全湍流用代数或单方程湍流模型计算。此外，自然过渡的过渡模型。在考虑风洞干扰效应后，定常跨音速气动特性的计算结果与Schewe的实验结果符合得很好。气动弹性计算预测极限环颤振与实验一致。颤振频率的计算值与实验值吻合较好，但颤振振幅的计算值比实验值大一个数量级。这种差异可能是由于计算中忽略了全部风洞干扰效应。
A numerical investigation of the transonic steady-state aerodynamics and of the two-degree-of-freedom bending/torsion flutter characteristics of the NLR 7301 section is carried out using a time-domain method. An unsteady, two-dimensional, compressible, thin-layer Navier–Stokes flow-solver is coupled with a two-degree-of-freedom structural model. Fully turbulent flows are computed with algebraic or one-equation turbulence models. Furthermore, natural transition is modeled with a transition model. Computations of the steady transonic aerodynamic characteristics show good agreement with Schewe's experiment after a simplified accounting for wind-tunnel interference effects is used. The aeroelastic computations predict limit-cycle flutter in agreement with the experiment. The computed flutter frequency agrees closely with the experiment but the computed flutter amplitudes are an order of magnitude larger than the measured ones. This discrepancy is likely due to the omission of the full wind-tunnel interference effects in the computations.