Lifting-line theory of swept wings based on the full potential theory

Abstract

The asymptotic theory of high-aspect-ratio transonic swept wings of Refs. [2–5] is extended to irrotational compressible flows based on equations of the full-potential theory. The formulation allows for imbedded supercritical flows with shocks; the results are applicable to oblique wings, swept-back as well as swept-forward wings, but restricted to planforms with centerlines composed of straight segments. The free-stream velocity is assumed to remain below the sonic speed. For a wing geometry generated from a single airfoil shape, the reduced system of 2-D equations admits solutions with similarity structures, permitting the problem to be solved only once for all span stations. The application of the theory is expected to lead to a substantial improvement over the earlier analysis of transonic swept wings based on the small-disturbance theory, concerning the accurate determination of inviscid drag and lift. The study provides also a basis for examining the influence of the trailing vortex sheet geometry, which are incompletely accounted for in current 3-D computer programs.