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Investigation of the Thwaites Airfoil Principle as Applied to Helicopter Rotor Blades

Report Number: WADC TR 53-497
Author: Arnold, L.
Author: Yuan, S. W.
Corporate Author: Lee Arnold Associates, Inc.
Laboratory: Aeronautical Research Laboratory
Date of Publication: 1954-01
Pages: 86
AD Number: AD0046678

A performance calculation has been carried out for the purpose of comparing the Piasecki XH-16 rotor vith the Karman-Yuan rotor. The two rotors ,atre asi%ned identical in size and lifting capacity (rotor diameter 82 ft, gross weight 36600 lbs). The Piasecki rotor blade is equipped with an NACA 0015 airfoil and the Karman-Yuan rotor blade vith an elliptical airfoil of 18% thickness chord ratio and cyclic flap control. The controllable lift distribution along the blade span of the Karman-Yruan rotor is achieved by varying the spanwise flap location and applied boundary layer suction. Due to the high lift coefficient employed in the Karman-Yuan rotor blade it was found that a lower rotational speed can be used to sustain the same gross wieght as does the XH-16.

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