A high-precision CFD method based on WENO(weighted essentially non-oscillatory)-piecewise linear scheme was established for numerical simulation on the rotor/fuselage aerodynamics interaction flow field. And it was suitable for the CFD solver of cell-centered scheme. The pressure coefficient on the surface of the fuselage of different rotor/fuselage model examples in forward flight was calculated by the method

and the calculation results were in good agreement with the experimental results

verifying the effectiveness of the calculation method. Then

the method was extended to simulate the flow field of X3 compound high-speed helicopter rotor/wing/propeller model in hover

and the flow field was compared with flow field of single rotor and rotor/wing model in hover. The results showed that the wing acted as a retarder on the downwash of rotor

causing the irregular flow under the wing. Furthermore

the slipstream of propeller and the downwash of rotor interfered with each other to produce a certain deflection

and the speed of downwash was faster than the speed of slipstream

the downward deflection of propeller slipstream was significant.