Investigation of time- and spatially-resolved surface pressures on an aeroelastically scaled aircraft model in low-speed, high-angle-of-attack conditions
J. Stegmüller(1), S. Hayböck(1), M. Hilfer(2), C. Breitsamter(1)
1: Chair of Aerodynamics and Fluid Mechanics, Technical University of Munich, Boltzmannstraße 15, 85748 Garching, Germany
2: Institute of Fluid Mechanics, TU Braunschweig, Universitätsplatz 2, 38106 Braunschweig, Germany
DOI:
This study investigates the unsteady aerodynamic surface pressures on a full-span, aeroelastically scaled, flexible aircraft model of double delta wing type focusing on lowspeed, high-angle-of-attack conditions. Experiments were conducted in the TUM-AER wind tunnel at 𝑀𝑎∞ = 0.15 using a synchronized measurement setup featuring fast-response pressure-sensitive paint and high-speed photogrammetry sampled at 5000 Hz. This work utilizes a sting-mounted full model, including fuselage, wings, horizontal tailplanes, and vertical fins, to capture flow phenomena associated with leading-edge vortex bursting and structural dynamics interactions. Comparisons between rigid and aeroelastically scaled configurations reveal distinct differences in flow topology; specifically, the rigid configuration exhibits a vortex breakdown location further upstream compared to the flexible case. The findings in this work highlight the critical role of fluid-structure interaction in determining buffet loads.
