A general method, based on two-dimensional crossflow concepts, is presented for obtaining the lift and moments on highly swept wings. Emphasis is placed on obtaining solutions for wings having swept trailing edges. The method is applicable for all problems where the velocity boundary conditions can be made homogeneous by differentiation in the streamwise or spanwise directions.
Lift, roll, and pitch solutions, for highly swept wings, are presented. Both direct problems (where the plan form is given) and inverse problems (where the shed vortex sheet is given) are considered. The solutions of the direct problems are expressed in terms of functions which are evaluated from integral equations. Some limiting solutions of the integral equations are indicated. Numerical results are given for wings having parallel leading and trailing edges.

A general method, based on two-dimensional crossflow concepts, is presented for obtaining the lift and moments on highly swept wings. Emphasis is placed on obtaining solutions for wings having swept trailing edges. The method is applicable for all problems where the velocity boundary conditions can be made homogeneous by differentiation in the streamwise or spanwise directions.
Lift, roll, and pitch solutions, for highly swept wings, are presented. Both direct problems (where the plan form is given) and inverse problems (where the shed vortex sheet is given) are considered. The solutions of the direct problems are expressed in terms of functions which are evaluated from integral equations. Some limiting solutions of the integral equations are indicated. Numerical results are given for wings having parallel leading and trailing edges.