Theoretical Spanwise Lift Distributions of Low-Aspect-Ratio Wings at Speeds Below and Above the Speed of Sound.

摘要

The spanwise lift distributions of wings of low aspect ratio but of arbitrary plan for and angle-of-attack distribution have been analyzed by two well-established concepts: the virtual-mass concept and the Weissinger method. Both concepts have been found to yield the same simple integral expression for the spanwise lift distribution in terms of the spanwise angle-of-attack distribution. Tables and figures of lift distributions of low-aspect-ratio wings have been presented. Within certain limitations these distributions are independent of the plan form. For plan forms with leading edges swept back behind the Mach cone, the results of the analysis are applicable at supersonic speeds.