Load Distribution on Multielement Deformed Airfoils with Gap Effects

Abstract

x,y, z a. A 6The aerodynamic loading for deformed wings with elevens in subsonic flow is considered. The solution procedure falls into the potential flow category with appropriate restrictions. Lifting surface Kernel function formulation is used in which the local pressure loading for both wing and elevon is determined simultaneously and written as a summation equation. The solution procedure allows closed-form results to be obtained for the elevon hinge moments. Cases under study include gaps between wing and elevon in addition to arbitrary wingelevon deformations. Fuselage effects and leading-edge suction are also used to apply results to a general configuration. Results for all cases compare very well with experimental data. Experimental data taken in a lowspeed wind tunnel are presented for a cropped delta wing and rectangular elevon in which the wing-elevon gap was the primary test variable.