Research on Rotor/Fuselage Aerodynamic Interaction Based on Viscous Vortex Particles Method

A numerical method for helicopter rotor/fuselage aerodynamic interaction has been established. Where the viscous vortex particle method is applied to model rotor wake and the vortex panel method is employed to model the aerodynamic charac-teristics of helicopter components such as blade, fuselage, horizontal stabilizer, et al. Then the vortex flow-field of rotor/fuselage interaction is simulated and analyzed based on the developed method. Meanwhile, through the comparison of rotor/fuselage aerodynamic interaction between the test data and calculation value, the effectiveness and accuracy of the developed method has been validated. Based on this, some meaningful conclusions are drawn.