Lift and profile-drag characteristics of an NACA 0012 airfoil section as derived from measured helicopter-rotor hovering performance
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Report presenting synthesized rotor-blade section lift and profile-drag characteristics for an NACA 0012 airfoil section as a function of angle of attack and Mach number for use in calculations of helicopter-rotor hovering performance are presented. At low tip Mach numbers, the synthesized data have higher maximum lift and lower profile drag at maximum lift than the equivalent two-dimensional airfoil data. Results regarding synthesized blade-section characteristics, rotor hovering characteristics, and rotor profile-drag torque are provided.