The panel method was used to simulate the helicopter fuselage flowfield.For the isolated fuselage of rotor body interaction (ROBIN) model

the pressure coefficient distribution along the top centerline was calculated in forward flight.The computational results were compared with the referenced data and computational fluid dynamics(CFD) results

validating accuracy of the methodology.Discrete vortices system was used to simulate the lifting surfaces

including horizontal stabilator

vertical stabilator and short wing.Aerodynamic interaction of fuselage

horizontal stabilator and vertical stabilator of UH-60 helicopter with short wing was computed and analyzed when the lifting surface parameters were adjusted.The results indicate that

change of the installation angle will have significant influence on the airflow around the lifting surface as the greatest influential parameter.Horizontal stabilator parameters

in particular the installation angle

can yield evident impact on the pressure coefficient of vertical stabilator and short wing

while decrease of the vertical stabilator span and increase of short wing installation angle can respectively increase their own pressure coefficient.