A high-resolution numerical simulation was carried out for the aerodynamic interference phenomenon between rotor and wing of the tilt-rotor aircraft in the conversion mode. The integral form unsteady Navier-Stokes equations are discretized by the finite volume method, and the relative motion between the rotor blade and the wing is processed by overlapping grids. The Cartesian structured grid based on the octree structure is adopted for background grids, and the grid self-adaptive technology based on the non-dimensional Q criterion is used to obtain high-resolution wake. First, the hover states of the isolated rotor and the rotor-wing combination are calculated. According to the calculation results, the accuracy for rotor aerodynamic prediction and the high-resolution characteristics for rotor wake structure evolution of high-resolution solver are proved. The calculation results of IDDES and RANS in the hovering state of rotor wing assembly are compared. The flow field obtained by IDDES is shown to be more accurate, and the aerodynamic results obtained with IDDES are also different from the RANS results. Subsequently, simulations of the flight states of rotor-wing assembly with different tilt angles in the conversion mode are carried out. Then, the aerodynamic interference flow field between the rotor and the wing is obtained and analyzed. The results show that the induced slipstream produced by the rotor in the middle of the conversion state has a certain lift gain effect on the wing, but there is no obvious lift gain at the beginning and end of tilt-state and there is even negative gain at the beginning. The aerodynamic variation of rotor and wing shows that rotor-wing aerodynamic interference in the conversion mode has an important influence on the aerodynamic performance of tilt-rotor.
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