Experimental Tests and CFD Simulations on a Tiltwing Aircraft in Hover

In the present work, the aerodynamic interaction between the rotor wake and the wing on a high-performance tiltwing aircraft operating in hover has been investigated. Both experimental and numerical approaches have been used to give a detailed description of the main physical phenomena related to this problem. The performance of the aircraft and the flow field between the wing and its rotor have been analysed making use of force and PIV (Particle Image Velocimetry) measurement techniques. High accuracy numerical simulations have been carried out by means of an in-house CFD (Computational Fluid Dynamics) code and both steady and time accurate calculations have been performed on the aircraft titled wing configuration. Numerical predictions have been validated by comparing the simulation results with experimental data and have been used to help the description of the flow field around the aircraft.