Rotor Aerodynamics:
Examples of Calculation

Fig. 1 shows the computed spanwise loading (lift coefficient) for the advancing and retreating blade of a helicopter rotor in advancing flight. Advance ratio=0.25; pitch angle=5 deg. Note the loss of balance during the half turn (180 deg). The reason for this behavior is explained in the dynamic stall section.

Fig. 1: Blade loading for advancing and retreating helicopter blade

Learn More

• More Rotor Calculations
• Lifting Surface Methods
• Unsteady Aerodynamics
• Dynamic Stall