Tests of the NACA 64-010 and 64A010 Airfoil Sections at High Subsonic Mach Numbers
Description:
Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.
Date:
July 8, 1949
Creator:
Hemenover, Albert D.
Item Type:
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