Lift-Cancellation Technique in Linearized Supersonic-Wing Theory

摘要

A lift cancellation technique is presented for determining load distributions on thin wings at supersonic speeds. The technique retains certain features of the method recently introduced by Theodore P. Goodman, while simplifying and generalizing others. A general expression is derived for the load distribution over a cancellation wing. This expression permits the determination of lift distributions on wings that cannot be solved by cancellation techniques based on the superposition of conical flows. The boundary conditions for either a subsonic leading edge or a subsonic trailing edge can be satisfied. Applications of the expression to swept wings having curvilinear plan forms and to wings having reentrant side edges are indicated.