Effects of compressibility on rotor hovering performance and synthesized blade-section characteristics derived from measured rotor performance of blades having NACA 0015 airfoil tip sections

James P. Shivers, Paul J. Carpenter
naca-tn-4356
Sep 1958


An investigation has been conducted at the Langley helicopter test tower to determine the low tip Mach number blade maximum mean lift coefficients and the high tip Mach number effects of compressibility for rotor blades having NACA 0015 tip airfoil sections was 1.15, as compare with 1.13 and 1.07 obtained previously with rotors having NACA 63 (sub 2)-015 and NACA 23015 airfoils sections, respectively.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1958/naca-tn-4356.pdf