The computational fluid dynamics (CFD) method based on unstructured grid sliding grid technology and the experiment method of aerodynamic interference were used to simulate the flow field of the quad tilt rotor (QTR) aircraft in helicopter mode. The aerodynamic characteristics of the QTR aircraft in vertical flight and the effect of some parameters on the aerodynamic characteristics were studied. Results showed that the interference between the front and rear rotors of the QTR aircraft was not obvious

but the interference between the rotor and the wing was greater; the interference of the rotor rotation direction on the rotor and the wing was different

the aerodynamic force of the wing accounted for 15% of the rotor thrust in the right rotation

and 9% of the rotor thrust in the left rotation; during the vertical motion of the QTR aircraft

the rotor lift and torque change could cause changes in component force and low/head-up torque in the forward direction; during the vertical descent of the QTR aircraft

the rotor could enter into the vortex ring state. The presence of the wing effectively reduced the destructive effect of the vortex ring state

and the vortex ring reduced the impact of the airflow on the wing tip.