Comparison Between Experimental Data and Helicopter Airloads Calculated Using a Lifting Surface Theory
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB
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Results of the calculation of helicopter airloads using a lifting surface theory solution are presented and compared with experimental data. These results indicate that a very accurate wake geometry model will be required in order to make full use of the accuracy of the lifting surface theory solution. It is observed that the experimental vortex induced loads decrease as the vortex moves inboard along the blade this phenomenon in the behavior of the vortex wake of a rotor requires more investigation.