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

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 theκ-εmodel. 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 tiltrotor 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 provides a basis for the research about the rotated layout of the tiltrotor aircraft