Some improvements are shown for the helicopter rotor code HERO. The code is based on a blade element method using relative simple inflow models and is presently being improved with respect to aerodynamic modeling. Experimental results are used to validate the performance characteristics and the inflow modeling. Calculations with the unsteady aerodynamics model of Leishman & Beddoes are shown. A preliminary empirical formula is presented to take rotational effects into account. The formula is implemented in a semi-empirical dynamic stall program, and a dynamic stall loop showing the influence of rotation is presented.
Validation of the Helicopter Rotor Code HERO
1993
23 pages
Report
No indication
English
Validation of the Helicopter Rotor Code HERO
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