Research On Rotor/Wing Aerodynamic Interaction For Tilt-rotor Aircraft

This paper was based on the Finite volume method of the computationalfluid dynamics and the dynamic reference frame method to simulate andanalyze the interference flow field between the rotor and the wing of thetilt-rotor aircraft. This flow field is unsteady and very complicated. It can betransformed the rotating unsteady problem into the stationary problem by usingthe dynamical reference frame method, and reduces the computation. Theprofile of the rotor is the NACA0012, the computational grid is theunstructured grid, the turbulence model is the k-ε model. By changing theangle of the rotor blade, the height between the rotor and the wing,and theangle of the wing, it’s obtained the variation of the pressure which the wingwas got.The results show that the airflow interference exists between the rotorand the wing of the tilt-rotor aircraft in the hovering condition. Because thedownwash flow is generated by the rotor of the tilt-rotor aircraft,The uppersurface of the wing suffers from the downwash flow shows an obviousmutation in a small range. The range of maximal pressure and the center pointof aerodynamic interference are strengthened by increasing rotor mountingangles. However, the position of the center point changes rarely. The range ofmaximal pressure and the center point of aerodynamic interference areincreased by reducing the relative height between the wing and the rotor of thetilt-rotor aircraft, and the position of the center point moves forward the bodyof the tilt-rotor aircraft. When changed the attack angle of the wing,the part ofthe wing that closed to the rotor was subjected to greater force, and the positionof the center point changed rarely. This law provided a basis for the researchabout the rotated layout of the tiltrotor aircraft.