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Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Frank T Abbott

Abstract

Report presenting tests in the two-dimensional low-turbulence pressure tunnel of a model of the NACA 66,2-116, a = 0.6 airfoil section representing the root section of the wing for the XP-63 airplane. The model was of 24-inch chord, built of wood with dural slot cover plates for the flap.

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Key concepts: Airfoil, Airplane, Wing, Chord (peer-to-peer), NACA airfoil, Section (typography), Structural engineering, Angle of attack