The Development of a Computer Aided Airfoil Design Procedure Including Preliminary Wind Tunnel Experiments on a Low Reynolds Number High Lift Section. Volume I.

摘要

An investigation on the state of the art of subsonic airfoil section design, including a review of the historical development of airfoil design methodology, was carried out. A computer aided airfoil design procedure employing current technology was developed and utilized to design a low-Reynolds number, high-lift airfoil section. Preliminary wind tunnel studies were carried out on this high-lift section and the influence of flow disturbances on its performances evaluated. This study represents the first phase in determining how changes in airfoil design parameters influence the dynamical properties of the airfoil. (Author)