Paraglider Wings of Small Conical Camber in Supersonic Flow.

Using the linearized supersonic wing theory a calculation method is developed for unyawed parawings with subsonic and supersonic leading edges. Conical configurations with and without keel are treated and the canopy surface is assumed to be an inextensional flexible membrane. A linear integral equation is established on which the solution of the problem is based. A special approximation with orthogonal polynomials is used for solving the integral equation in the elliptic regions similar to usual quadrature methods in lifting wing theory. The integral equation for the hyperbolic region can be transformed in a differential equation which is integrated in closed form.