Helicopter blade aerofoil

摘要

Upper and lower surfaces of an aerofoil are defined by the following coordinates given in the table below, and the configuration of a leading edge of the aerofoil is defined by the following leading edge radius and the center of circle. Thus drag divergence Mach number Mdd and maximum lift coefficient Clmax can be increased and the noise level can be reduced. Leading edge radius r/C =0.01073 Center of circle X/C=0.01072, Y/C=-0.00373