In order to explore the aerodynamic change law of a certain type of quad tilting rotor unmanned aerial vehicle (UAV)

during high-speed cruising process, the multiple reference frame (MRF) numerical simulation method is used to

analyze the quad tilting rotor UAV model established in this paper. By changing the relative thickness of the wing

airfoil, rotor collective pitch, forward flight speed and other parameters, the whole aircraft disturbance of the UAV

model is simulated, and the aerodynamic change characteristics of components such as rotors are analyzed. The results show that increasing the relative thickness of the wing airfoil can reduce the pull coefficient of rear rotor during cruise process, When the thickness increases by 6%, the tensile coefficient decreases by 17.09%. At the same

time, under the superposition of the front intake air flow and the front rotor slip flow, the front rotor slip flow will

have a certain impact on the rear rotor aerodynamic performance, and as the forward flight speed increases, the impact of the front rotor slip flow will first increase and then weaken.

quad tilting rotor (QTR), aerodynamic disturbance of unmanned aerial vehicle, slip flow, propeller efficiency