Helicopter blade aerofoil and helicopter blade

摘要

Upper and lower faces of a helicopter blade aerofoil are defined by the following coordinates. X/CYup/CYlow/CX/CYup/CYlow/CX/CYup/CYlow/C0.000000.000000.000000.050000.03891-0.017140.550000.05943-0.032110.001000.00511-0.005840.075000.04682-0.018620.600000.05498-0.030840.002500.00843-0.008130.100000.05291-0.019790.650000.04968-0.028830.005000.01218-0.010140.150000.06152-0.022060.700000.04349-0.026000.007500.01505-0.011360.200000.06666-0.024700.750000.03649-0.022370.010000.01747-0.012180.250000.06892-0.027290.800000.02886-0.017940.012500.01959-0.012770.300000.06895-0.029490.850000.02087-0.013150.015000.02150-0.013280.350000.06841-0.031090.900000.01279-0.007770.017500.02325-0.013750.400000.06744-0.032110.950000.00538-0.003040.020000.02487-0.014150.450000.06568-0.032701.000000.00236-0.000950.025000.02780-0.014830.500000.06301-0.03272leading edge radius r/C = 0.0096center of circle X/C = 0.0097, Y/C=-0.0018;Accordingly, the maximum lift coefficient Clmax is large in a wide velocity range from lower velocity to higher velocity, and reduction of noise level and pitching moment can be achieved.