Calculated spanwise lift distributions and aerodynamic influence coefficients for swept wings in subsonic flow

Report presenting spanwise lift distribution calculations for 61 swept wings with various aspect ratios and taper ratios and with a variety of angle-of-attack or twist distributions, including flap and aileron deflections, by means of the Weissinger method with eight control points on the semispan. Also calculated were the aerodynamic influence coefficients which pertain to a certain definite set of stations along the span.