Aerodynamic theory for a cascade of oscillating airfoils in subsonicflow
Aerodynamic theory for a cascade of oscillating airfoils in subsonicflow
复制标题
亚音速流中级联振荡翼型的空气动力学理论
DOI：
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发表时间：
1976
期刊：
影响因子：
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通讯作者：
J. A. Moore
中科院分区：
文献类型：
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作者：
W. Jones;J. A. Moore
该理论是在速度势而不是加速度势方面发展起来的，并给出了一个简单的数值方法的简要概述。不同的翼型间距，频率，马赫数，安装角，相邻翼型之间的相位差的影响进行了讨论。特别注意的是，在纯垂直平移和俯仰运动的气动阻尼的变化。结果表明，平移阻尼可以成为零，在某些离散频率，但它永远不会成为负的。然而，俯仰力矩阻尼在实际感兴趣的很宽的频率范围内可以变为负值。翼型假定为零平均冲角。
The theory is developed in terms of the velocity potential rather than the acceleration potential, and a brief outline is given of the simple numerical technique used. The effects of varying airfoil spacing, frequency, Mach number, stagger angle, and phase difference between adjacent airfoils are discussed. Particular attention is given to variations in the aerodynamic damping for pure vertical translational and pitching motions. It is shown that the translational damping can become zero at certain discrete frequencies but that it never becomes negative. The pitching moment damping, however, can become negative over a wide range of frequencies of practical interest. The airfoils are assumed to be at zero mean incidence.