APPROXIMATE SOLUTIONS FOR COMPUTING HELICOPTER HARMONIC AIRLOADS
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB
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Assuming a constant circulation, rigid, trailing wake and using a lift deficiency function to represent the unsteady aerodynamic effects, various methods of calculating the airloads on a helicopter rotor in steady, forward flight were developed for the purpose of achieving a faster solution times for a given level of accuracy and b a more accurate representation of the lifting surfacevortex interaction for the case where the blade passes close to the vortex line generated by a previous blade. Since most of the solution time is required to calculate the induced velocities due to the trailing wake, various approximate methods of calculating the induced velocities due to a rigid, skewed helix were developed.