9-2. Unsteady configurations
Leading edge flow quality sensitive to rotor blade angle of attack variations
Blades with cyclic nose droop for improved helicopter rotor design
Separation reduction by airfoil nose droop in flow with high angle of attack |
Nose droop plus local surface flattening near leading edge avoid shock-induced separation |
Delay of separation onset by leading edge modification |
Experimental setup for nose droop concept verification |
