Abstract
A simplified procedure is presented for the design of a leading-edge fairing of a wing-body combination. The design aims at optimizing the design of the fairing, which is to serve the double purpose of eliminating separation near the wing-body junction, as well as minimizing leading-edge contamination of the laminar wing. The design optimization procedure is based on the analysis of the viscous-flow performance of a fairing of prescribed geometry. First, a panel method is used to determine the inviscid flow around the fairing. This is then followed by an integral-method calculation of the boundary-layer development on the attachment line along the body and the fairing. As an application, a fairing was designed for a straight NACA0015 wing mounted on a flat plate. Tests in the wind tunnel confirmed the effectiveness of the fairing
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
