A helicopter rotor in hover conditions out of ground effect as well as in ground effect is studied numerically by means of an URANS approach. Tip vortex geometrical positions as well as thrust coefficients are scrutinized and compared to reference data in literature. Parameter variations are done in the rotor/ground plane distance in the range of h/R = 0.32...0.84 and collective angles of the rotor blades between 13 ... 17. Generally, very good agreement with the experiment is achieved.
CFD Calculation of a Helicopter Rotor Hovering in Ground Effect
2013
8 Seiten
Conference paper
English
Unsteady Aerodynamics of Helicopter Rotor Hovering in Dynamic Ground Effect
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