Numerical Calculation Of Rotor Performances In Real Flight Configurations

Rehbach's vortex particle method used for translating lifting surfaces has been extended here to unsteady incompressible flows around interacting bodies in relative motion. For this purpose a time upwinding method (T. U. B) has been implemented in order to minimize computational cost. The body surfaces are modeled with quadrangular panels over each of which a normal doublet intensity is kept constant. The free vortex domain is represented with a set of vortex carrying particles. As numerical examples, we recall results obtained for a three-bladed rotor in hover. Then, results about a eight-bladed propeller interacting with an axisymmetric hub are presented. For a twobladed rotor in three flight configuration cases without flapping, with flapping and with interaction between the flapping rotor and a fuselage, a time upwinding method has been implemented. The effects of the different configurations are compared.