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Delta wings are highly-swept planforms useful for flight conditions where high-maneuverability is required. Due to the sweep angle on the wing, strong vortices are formed that can generate increased lift at specific angles of attack. Current interest among the aerodynamics community is in a class of delta wings whose flow field exhibit increased complexities, but are desirable for micro air vehicle applications.
This project is an experimental study of a type of low-sweep delta wing planform, performed within a low-speed, subsonic wind tunnel. The primary measurements to be performed will include tufts visualization (taping threads to the wing surface), aerodynamic load measurements, and hot-wire measurements. The student is expected (under supervision) to research the current literature, design wind tunnel models, perform the experiments, and document results.
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