Paul J. Carpenter
Synthesized rotor-blade section lift and profile-drag characteristics for 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. Measured rotor hovering performance from which the major portion of the synthesized data was derived is presented for a range of tip Mach numbers from 0.28 to 0.70. The synthesized data presented for Mach numbers from 0.70 to 0.88 were derived from a previous investigation of another blade having an NACA 0012 airfoil section at the tip.
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