Rotor-fuselage interactions are of main interest for the design of helicopter airframes. The periodic loads can indeed affect the fuselage structure and have an impact on the noise and vibrations levels.
In this study, FINE™/Open CFD software was used to simulate the NASA ROBIN helicopter test case in hover flight conditions. The NASA ROBIN test case is a wind tunnel test campaign performed on a generic helicopter fuselage model designed for the study of the rotor-fuselage interactions. The periodic pressure measurements on the helicopter body were obtained at NASA Langley wind tunnel installations and covered a range of rotor thrust conditions, as well as different helicopter flight conditions.
An excellent agreement was observed between the experimental results and the FINE/Open CFD unsteady simulation of the hover flight.
The figures show the periodic variations of the fuselage pressure coefficient as a function of the azimuthal position of the main rotor and the animation of static pressure on the fuselage and rotor blades.