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Two-dimensional wind-tunnel investigation of an NACA 64-009 airfoil equipped with two types of leading-edge flap

Felicien F Fullmer

Abstract

Report presenting an investigation to determine the effect of leading-edge flaps on the maximum lift coefficient of an NACA 64-009 airfoil and to compare the results with data obtained from previous testing of a similar flap. Two types of flaps, one intended to slide forward on the upper surface and one hinged at the center of the airfoil leading-edge radius, were tested. Results regarding lift characteristics, pitching-moment characteristics, and effect of leading-edge roughness are provided.

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Available abstract

Key concepts: Airfoil, Leading edge, Lift coefficient, Aerodynamic center, Lift (data mining), Wind tunnel, Enhanced Data Rates for GSM Evolution, Pitching moment