Abstract
Wind-tunnel tests were performed on a I-scale model of a general aviation trainer configuration in the NASA Langley 12-Foot Low-Speed Tunnel. The purpose of these tests was to investigate the configuration's high-angleof-attack characteristics as well as the low-speed stability and control characteristics. The focus of the highangle-of-attack testing was to develop leading-edge modifications that would tailor the stall characteristics of the model. The testing resulted in two different leading-edge modifications. A small profile leading-edge droop on the outboard 29% of the wing was developed that kept the outboard wing flow attached to high angles of attack, resulting in increased roll damping and added aileron authority. The second leading-edge modification developed was a large profile leading-edge droop on the outboard 50% of the wing. This large droop kept the outboard wing flow attached to very high angles of attack that greatly improved the roll damping characteristics and stall/departure resistance as well as provided large increases in aileron authority.
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