摘要
基于运动嵌套网格的欧拉方程建立了旋翼流场的数值模拟方法。以旋翼气动性能仿真结果作为输入,应用FARASSATE1A公式发展了适用于旋翼气动噪声的计算程序。通过与C-T旋翼的实验数据对比,验证了方法的有效性。在此基础上,通过改变旋翼桨叶翼型的厚度、弯度以及最大弯度位置研究了翼型参数对旋翼悬停气动噪声特性的影响。研究结果表明,翼型厚度是决定旋翼厚度噪声的关键因素,旋翼载荷噪声决定于旋翼桨叶表面压力分布。旋翼厚度噪声主要受翼型厚度变化影响,旋翼载荷噪声则主要受翼型最大弯度和最大弯度位置的影响。翼型参数变化不会明显改变旋翼气动噪声的方向特性。
A numerical simulation of rotor flow-field was proposed based on the unsteady Euler equations with moving chimera grid. Calculation procedure predicting helicopter rotor aerodynamic and noise was developed using the formula of FARASSATE1 A and making simulation results of rotor aerodynamic performance as an input. A comparison against the experimental data of C-T rotor verified the availability of the simulation. The effects of airfoil parameters on rotor acoustics were analyzed by changing airfoil thickness,camber,and max camber position. The results showthat airfoil thickness is a crucial influence factor for rotor thickness noise. The loading noise highly depends on the pressure distribution of blade surface,associated with biggest bending of airfoil and its position. The airfoil parameters of rotor blade do not remarkably change the directivity of thickness and loading noise.
出处
《沈阳航空航天大学学报》
2016年第4期1-8,共8页
Journal of Shenyang Aerospace University
基金
国家自然科学基金(项目编号:51307004)
关键词
翼型参数
旋翼流场
旋翼气动
旋翼噪声
方向特性
airfoil parameter
rotor flow-field
rotor aerodynamic
rotor acoustic
directivity