Aerodynamic optimization of the flat-plate leading edge for experimental studies of laminar and transitional boundary layers

• DOI: 10.1007/s00348-012-1324-2
• Publication Date: 2012-06-11T11:53:52Z
• Authors: Ronald E. Hanson; Howard P. Buckley; Philippe Lavoie
• Keywords: 0103 physical sciences; 01 natural sciences

This work is concerned with the design of a leading edge for a flat-plate model used to study laminar and transitional boundary layers. For this study, the flow over the complete boundary-layer model, including leading edge, flat section, and trailing-edge flap, is modeled. The effect of important geometrical features of the leading edge on the resulting pressure distribution, starting from the well-known symmetric modified super ellipse, is investigated. A minimal pressure gradient on the measurement side of the plate is achieved using an asymmetrical configuration of modified super ellipses, with a thickness ratio of 7/24. An aerodynamic shape optimization is performed to obtain a novel leading edge shape that greatly reduces the length of the non-zero pressure gradient region and the adverse pressure gradient region compared to geometries defined by ellipses. Wind tunnel testing is used to validate the numerical solutions.