Abstract:
Summary. A series of low drag aerofoils, modelled roughly on the NACA 6-series, is described. It appears to offer theoretical advantages over its progenitor, and allows flexibility in the choice of leading-edge thickness and trailing-edge angle. Aerofoils of this series are specified by five parameters, and the aerodynamic and geometrical characteristics of about 1000 of the sections are listed. The mathematical derivation of their shape (by the Lighthill method) is described in detail, and an ALGOL 60 procedure for the computation of their ordinates is included ; care has been taken to construct this procedure so that it may be of general use in other applications of the Lighthill method of design.