Preliminary Investigation in the NACA Low-Turbulence Tunnel of Low-Drag Airfoil Sections Suitable for Admitting Air at the Leading Edge

摘要

A thickness distribution having the desired type of pressure distribution was found from tests of a flexible model. Other airfoil shapes were derived from this original shape by varying thickness, camber, leading- edge radius, and size of leading-edge opening. Data are presented giving characteristics of these airfoil shapes in the range of lift coefficients for high speed and cruising speed. Measurements of maximum lift characteristics were made for high speed and cruising speed. Measurements of maximum lift characteristics were made for only a few configurations, and no conclusions could be drawn as to what effect leading-edge openings would have on maximum lift characteristics of complete wing.