Investigation into the Three-Dimensional Stall Development on a Modified NACA 23012 Aerofoil

摘要

A numerical method of modifying the trailing edge upper surface pressure gradient of a given airfoil was applied to the NACA 23012 airfoil to enhance the trailing edge pressure gradient. The redesigned airfoil was tested in a subsonic wind tunnel. A flow visualization technique, using a fluorescent yellow oil-film, was used to indicate transition regions, laminar separation bubbles, and the positions of turbulent separation. The extent of three-dimensionality, reverse flow, and corner flow separation were also observed. Results show increased boundary layer separation of the modified airfoil, and vindicate the design method.