The main advantage of the method presented in Part I of this paper is the generality with regard to the shape of the wing plan form. This is a welcome innovation in the field of supersonic wing theory, where methods of solution of the usual lifting problem are restricted to a limited number of wing shapes. Most of the lifting characteristics of wings are now known at supersonic speeds, but the range of wings with curved subsonic leading and trailing edges needs further investigations. Therefore it seems that the extension of the design problem to include these lifting problems is a useful addition to the extensive literature on the subject.