Finite Element Simulation of Helicopter Rotor in Hover

Abstract

This work deals with the application of a devoloped compressible Navier-Stokes finite element code to flow around helicopter's configurations. This is one of the first trials to apply this kind of numerical technique in this area where it is very common to find finite differences and finite volumes results. This study is part of a project that includes several stages of devolpment covering from single rotor simulation in vertical and forward flight, interaction with fuselage, aeroelasticity, to the final goal which is the prediction of the aeroacoustic behaviour of the system and to diminish the noise generated by the counpling between fluid dynamic patterns. So, this problem contains a lot of interesting and challenging parts mostly under research. Here our concern is centered on the simulation of helicopter in hover condicition including a preliminar study of the fluid dynamic phenomenon specially that concerned with blade vortex interaction in vertical flight. A video with the simulation results is presented.