Work continues on the projects of developing general aviation wings which can be laterally controlled into and through the stall. In 1989 a paper was presented which suggested that lateral control of a wing, and possibly additional lift at angles of attack above stall, could be obtained by use of hinged control surfaces at the leading-edge near the wing tips. This idea was pursued using a flow visualization model in the water tunnel and a reflection plane wind tunnel model. Both models used a modified NFL airfoil section and leading-edge and trailing-edge ailerons. The wind tunnel tests included both force and pressure distribution tests. A summary of these results is presented as well as outline of wing tip surveys currently going on in the water tunnels.
Experimental Studies of General Aviation Wings at High Angles of Attack (Abstract Only)
1991
1 pages
Report
Keine Angabe
Englisch
Aircraft , Test Facilities & Equipment , Aerodynamics , Angle of attack , General aviation aircraft , Hydraulic test tunnels , Lateral control , Wind tunnel models , Wind tunnel tests , Wings , Ailerons , Airfoil profiles , Control surfaces , Flow visualization , Leading edges , Pressure distribution , Trailing edges , Wing tips
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