Calculation and analysis of interaction flowfield over tiltrotor aircraft in conversion mode

Abstract

Aiming at solving the complicated aerodynamic interaction problem of conversion mode, the preconditioning method is applied. Combined with the unstructured hybrid technique and the overlapping grid interpolation technique, a numerical simulation method for tiltrotor aircraft in conversion mode is established. On this basis, the validity of the numerical method is verified. Then, with the numerical simulation of isolated rotor, isolated fuselage and tiltrotor aircraft, the laws of the aerodynamic interaction of rotor/fuselage/wing/tail are analyzed with tilting process. The calculation results show that the rule of the influence of the rotor wake on the aerodynamic performance of the wing is different between the inner side and the outer side of the wing. Compared with the isolated rotor, the thrust coefficient of the rotor of the aircraft increases slightly by 0 ∼ 5% during the tilting process due to wing and the fuselage.