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Tests of the NACA 0010-1.50 40/1.051 airfoil section at high subsonic Mach numbers

Albert D Hemenover

Abstract

Memorandum presenting the aerodynamic characteristics of the NACA 0010-1.50 40/1.051 airfoil section as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. The results are compared with those of the effects of leading-edge-radius variation from 0.27 to 1.10 percent of the chord on the characteristics of a 10-percent-thick, symmetrical airfoil section at high subsonic Mach numbers. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

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Available abstract

Key concepts: Airfoil, Mach number, Drag divergence Mach number, Chord (peer-to-peer), NACA airfoil, Pitching moment, Angle of attack, Aerodynamics