TY - GEN
T1 - Icing effect on the aeroacoustics of helicopter blade-vortex interaction; a numerical study using large-eddy simulation
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=78649574892&partnerID=8YFLogxK
M3 - Conference article
AN - SCOPUS:78649574892
SN - 9781600867446
T3 - 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)
BT - 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)
T2 - 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)
Y2 - 7 June 2010 through 9 June 2010
ER -