Numerical Study of Fuselage Impact on Acoustic Characteristics of a Helicopter Rotor

The paper presents the results of simulation unsteady turbulent flow generated by helicopter main rotor in presence fuselage with an emphasis on analysis influence rotor-induced and rotor-generated acoustic field. Reynolds-averaged Navier–Stokes equations Spalart–Allmaras turbulence model are used to simulate Caradonna–Tung ROBIN interaction hovering flight. governing discretized using vertex-centered control volume method mixedelement unstructured meshes sliding mesh technology treat rotor. field rotor+fuselage is comparatively analyzed against case isolated It found that significantly changes acoustics. In particular, noticeably distorts directivity radiation increases overall sound pressure level under up 20 dB, emphasizing importance