NACA-MR-L5L11

Abstract

<strong>INTRODUCTION</strong> <br>At the request of the Bureau of Aeronautics, Navy Department, test were conducted in the Langley two-dimensional, low-turbulence tunnels of three 24-inch-chord airfoil models representing the root and tip airfoil sections and an intermediate airfoil section of the proposed Chance-Vought XF6U-1 airplane. The airfoils tested were the NACA 65(215)-114 (root section), the NACA 651-212, a = 0.6 (tip section), and an intermediate section taken at approximately 55 percent of the semi-span. The models of the root and intermediate sections were equipped with slotted flaps. <br>The tests included the determination of the aerodynamic characteristics of the three plain airfoil sections in both the smooth condition and with standard roughness applied to the leading edge. Lift tests of the root and intermediate airfoil sections were made for a range of flap deflections extending from 0^o to 50&#176;. Most of the data were obtained at a Reynolds number of&#160; 9 x 10⁶ although comparison tests were conducted at Reynolds numbers of 1 x 10⁶, 3 x 10⁶ and 6 x 10⁶.