Design Considerations for a UCAV Wing for Subsonic and Transonic Aeroelastic and Flight Mechanic Wind Tunnel Tests

In the German Aerospace Center, DLR, an internal project has been launched to investigate different UCAV configurations. One aspect, covered by the Institute of Aeroelasticity and the Institute of Aerodynamics and Flow Technology, is the wind tunnel test of a UCAV wing in subsonic and transonic flow. The model shall show measurable static aeroelastic deformations. Main goals of the tests will be the study of vortex-dominated flow on aeroelastic deformable wings, and the generation of data for the validation of numerical fluid-structure coupling for delta wings at various points of the operational envelope. At the same time, a new active wind tunnel support will be build to include a means of investigation into the flight mechanics of such a configuration. Contrary to many aeroelastic experiments, flutter tests are not part of the test program.