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
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