LIMIT-CYCLE-OSCILLATION EXPERIMENTS AT A TRANSPORT AIRCRAFT WING MODEL

Experiments have been performed in order to explore the Limit-Cycle Oscillation (LCO) behavior of a transport aircraft wing at transonic airspeeds. Therefore an aeroelastically scaled model of the outer part of a typical wing has been designed for investigations in a wind tunnel. The research model has a supercritical airfoil and an aspect ratio of 3.68 with a leading-edge sweepback angle of 32°. The static and dynamic structural properties as well as the aerodynamic shape of the wing model are reported. Experiments have been conducted in order to determine its static aeroelastic behavior. The LCO behavior can be investigated depending on several inflow parameters. The research model provides an excellent opportunity for investigating the governing physics of LCOs due to its properties and its instrumentation