A New Family of Low Drag Wings with Improved CL-ranges

摘要

A method is described of designing symmetrical aerofoils when reasonable values have been pre-assigned to the thickness/chord ratio, the Cj-range (defined below) and the leading-edge radius of curvature, gL. It produces aerofoils with GVranges larger than those of any previous'aerofoils the same thickness-choid latio. The method requires some aerofoil to start with;it is most'convenient to take a " rooftop "x as the initial one, since the primary considera¬tions of the thickness/chord ratio, position of maximum suction and tail-shape are most easily dealt with by the rooftop method.