EXPERIMENTAL AND NUMERICAL INVESTIGATION OF A STRUCTURAL-DYNAMICALLY SCALED DELTA WING WITH TRAILING EDGE FLAPS

This work focuses on an experimental investigations of a delta wing fuselage configuration in the low-speed wind tunnel W/T-A facility of the Chair of Aerodynamics and Fluid Mechanics at the Technical University of Munich. The influence of different trailing edge flap deflections on the aerodynamic characteristics is studied. For the aerodynamic analyses, force and moment measurements, Particle Image Velocimetry (PIV) measurements and a Fast Response Aerodynamic Probe (FRAP) measurement are conducted. A power spectral density analysis of velocity and pressure fluctuations is used to detect dominant frequencies of the two emerging vortex systems above the wing and compared to an analytical prediction method. Additionally, the wing is designed to be aeroelastically scaled. Thus, the deformation of the model is also investigated applying a photogrammetry measurement setup. At last, a comparison with aeroelastic simulations is conducted.