Flow Structure Interaction on Flexible UCAV Wing Platforms
Final rept. 1 Jul 2002-18 Jan 2006
EUROPEAN OFFICE OF AEROSPACE RESEARCH AND DEVELOPMENT FPO NEW YORK 09510
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This report results from a contract tasking University of Bath as follows The next generation of unpiloted combat air vehicles UCAVs will likely have flexible delta wings and will likely need the capability to perform extreme maneuvers at high gs. Vortical flows over delta wings produce periodic aerodynamic excitation which may cause unacceptable buffeting of a flexible wing structure. In this effort the contractor will investigate unsteady vortex flows over flexible delta wings, their interaction with the wing, and possibility of flow control by structural tuning. Basic research issues related to fluidstructure interactions for vortical flows will be addressed in analytical modeling, water tunnel testing, and wind tunnel testing. Wingtip accelerations will be measured using multiple accelerometers. PIV and LDV measurements will be used to capture the steady and unsteady phenomena in the wing flow field. The model geometry of the delta wing is simple, hence the experimental results may serve as benchmark tests for computational simulations.
- Pilotless Aircraft
- Structural Engineering and Building Technology