TY - GEN
T1 - LES studies of helicopter blade-vortex mechanism of interaction; the icing effect
AU - Ilie, Marcel
PY - 2010
Y1 - 2010
N2 - The influence of icing effect on the helicopter blade-vortex mechanism of interaction is investigated using large eddy simulation (LES). The simulations were performed for a Reynolds number, Re = 1.3 × 106, based on the chord, c, of the airfoil (NACA0012). Computations are carried out to investigate the influence of the icing effect on the aerodynamic coefficients and acoustic field. It was observed that the icing effect influences the aerodynamic coefficients in a specific manner. Larger amplitudes of aerodynamic coefficients were observed for the case of an iced leading edge when compared with the clean NACA0012 case.
AB - The influence of icing effect on the helicopter blade-vortex mechanism of interaction is investigated using large eddy simulation (LES). The simulations were performed for a Reynolds number, Re = 1.3 × 106, based on the chord, c, of the airfoil (NACA0012). Computations are carried out to investigate the influence of the icing effect on the aerodynamic coefficients and acoustic field. It was observed that the icing effect influences the aerodynamic coefficients in a specific manner. Larger amplitudes of aerodynamic coefficients were observed for the case of an iced leading edge when compared with the clean NACA0012 case.
UR - http://www.scopus.com/inward/record.url?scp=78649902488&partnerID=8YFLogxK
M3 - Conference article
AN - SCOPUS:78649902488
SN - 9781600867392
T3 - 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
BT - 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
T2 - 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
Y2 - 4 January 2010 through 7 January 2010
ER -