倾转旋翼机旋翼与机翼干扰数值模拟分析

Numerical Analysis of Aerodynamics Interference between the Rotor and Wing of the Tiltrotor Aircraft

基于计算流体力学有限体积法及动参考系方法,对倾转旋翼机旋翼/机翼干扰流场进行了数值模拟和分析。倾转旋翼机旋翼/机翼干扰流场是非常复杂的非定常流场,采用动参考系方法能将旋转非定常问题转化为定常问题,减小了计算量。旋翼翼型为NACA 0012,计算网格为非结构网格,湍流模型为κ-ε模型,通过改变旋翼桨叶安装角,得出机翼所受压力的变化规律。计算结果表明:悬停状态下,倾转旋翼机旋翼与机翼之间存在气流干扰,其中机翼的上表面受到旋翼下洗气流的压力,沿展向呈曲线分布;机翼上表面受到旋翼下洗气流的气动干扰,中心点压力和最大压力范围随旋翼安装角的变化增大,但中心位置变化不大。这一规律为倾转旋翼机的倾转布局研究提供了依据。

Based on the finite volume method of the computational fluid dynamics and the dynamic reference frame method, this paper simulates and analyses the interference flowfield between the rotor and the wing of the tiltrotor aircraft. The flowfield between the rotor and the wing of the tiltrotor aircraft is a very complicated and it＇ s not steady. Using the dynamical reference frame method can transform the rotating unsteady problem into stationary problem, reducing the amount of calculation. Rotor profile is the NACA 0012, computational grid is the unstructured grid and the turbulence model is theK - emodel. By changing the angle of the rotor blade, it obtains the variation of the pressure which the wing bears. The results show that the airflow interference exists between the rotor and the wing of the tihrotor aircraft in the hovering condition. The upper surface of the wing suffers form the downwash flowfield of the rotor and the pressure shows a curve distribution . The more the angle of the rotor blade increases, the more the pressure in the center point of the aerodynamic interference and the range of the maximal pressure increases, but the position of the center point changes rarely. This law orovides a basis for the research about the rotated layout of the tihrotor aircraft