SECTION CHARACTERISTICS OF THE NACA 0006 AIRFOIL WITH LEADING-EDGE AND TRAILING-EDGE FLAPS

摘要

A wind-tunnel Investigation was made to determine the section characteristics of the NACA 0006 airfoil equipped with a 0.15-chord leading-edge flap and a 0.30-chord trailing-edge flap. Lift and pitching-moment characteristics are presented for leading-edge flap deflections of 0°, 10°, 20°, 25°, 30°, 35°, 40°, and 50° with the plain trailing-edge flap deflected 0°, 35°, and 50°. Data are also presented for plain trailing-edge flap deflections of 20° and 70° with the leading-edge flap undeflected. Pressure-distribution data are presented in tabular form for the airfoil with various combinations of leading-edge and trailing-edge flap deflections. The data were obtained at a Mach number of 0.15 and a Reynolds number of 4,500,000.