Incipient torsional stall flutter aerodynamic experiments on a swept three-dimensional wing
Incipient torsional stall flutter aerodynamic experiments on a swept three-dimensional wing
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后掠三维机翼的初期扭转失速颤振空气动力学实验
DOI：
10.2514/3.23732
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发表时间：
1994
影响因子：
1.9
通讯作者：
F. Carta
中科院分区：
文献类型：
--
作者：
P. Lorber;F. Carta
为了加深对螺旋桨叶片扭转失速颤振问题的理解，对失速附近小幅度俯仰运动的空气动力学进行了实验研究。模型机翼在广泛且具有代表性的条件范围内以几个小幅度进行俯仰振荡。测量并积分非稳态表面压力以确定五个展向站的气动阻尼。对于所有研究的降低频率、马赫数和扫角，发现以静态失速为中心的运动存在强负阻尼。发现 30 度后掠配置几乎同时在整个翼展上变成负阻尼，而未后掠模型则表现出局部负阻尼区域，随着平均攻角的增加，该区域向翼尖移动。
The aerodynamics of small amplitude pitching motions near stall have been studied experimentally in order to improve understanding of the torsional stall flutter problem for propeller blades. A model wing was oscillated in pitch at several small amplitudes over a wide and representative range of conditions. Unsteady surface pressures were measured and integrated to determine the aerodynamic damping at five spanwise stations. Strong negative damping was found for motions centered near static stall for all studied reduced frequencies, Mach numbers, and sweep angles. The 30-deg sweptback configuration was found to become negatively damped over the entire span nearly simultaneously, while the unswept model exhibited local regions of negative damping that moved toward the wing tip as the mean angle of attack was increased.