Formulae for calculating the camber surfaces of thin swept-back wings of arbitrary plan-form with subsonic leading edges, and specified load distribution

Abstract

Formulae for calculating the-gradients and ordinates of the camber surfaces of swept-back wings of arbitrary plan-form with subsonic leading edges, and specified load distribution, are given, including those which have been programmed and used for DEUCE calculations for some swept-back and M-wings with curved leading edges. Some methods for the numerical calculation of singular integrals are given. For polygonal wings with simple load distributions, the equation of the camber surface is given in closed form. This is useful for obtaining approximate results for more general plan-forms.