Aerodynamic Characteristics and Topology of Interfering Vortex Systems at Hybrid-Delta Wings

High-agility aircraft often perform flight maneuvers at high angles of attack and angles of sideslip. For these configurations, a comprehension of the vortex development, interaction, and breakdown at sideslip conditions is crucial. In this study, two generic, low-aspect-ratio, hybrid-delta-wing configurations are investigated. A triple-delta-wing and a double-delta-wing configuration are discussed. Force and moment measurements, particle image velocimetry, and oil-flow visualization tests are conducted to resolve the vortex-dominated flowfield extensively. The flow separates at the sharp leading edges, and vortices are formed. For an angle of sideslip, the effective leading-edge sweep on the windward side is reduced and on the leeward side increased. This leads to a more stable vortex system on the leeward side and a destabilization on the windward side. Therefore, significant lateral instabilities occur at high angles of attack. © 2022 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc.,.     «

High-agility aircraft often perform flight maneuvers at high angles of attack and angles of sideslip. For these configurations, a comprehension of the vortex development, interaction, and breakdown at sideslip conditions is crucial. In this study, two generic, low-aspect-ratio, hybrid-delta-wing configurations are investigated. A triple-delta-wing and a double-delta-wing configuration are discussed. Force and moment measurements, particle image velocimetry, and oil-flow visualization tests are c...     »

Funding text This project is funded by the Deutsche Forschungsgemeinschaft (DFG, German Research Foundation), grant number BR1511/13-2. The fruitful cooperation with Airbus Defense and Space is gratefully acknowledged. Furthermore, the authors thank the German Aerospace Center (DLR) for providing the DLR TAU-Code used for the numerical investigations. Moreover, the authors gratefully acknowledge the Gauss Centre for Supercomputing e.V. (https://www.gausscentre.eu) for funding this project by providing computing time on the GCS Supercomputer SuperMUC at Leibniz Supercomputing Centre (https://www.lrz.de). The authors also highly appreciate the previous wind tunnel tests by Stefan Pfnür.     «

Funding text This project is funded by the Deutsche Forschungsgemeinschaft (DFG, German Research Foundation), grant number BR1511/13-2. The fruitful cooperation with Airbus Defense and Space is gratefully acknowledged. Furthermore, the authors thank the German Aerospace Center (DLR) for providing the DLR TAU-Code used for the numerical investigations. Moreover, the authors gratefully acknowledge the Gauss Centre for Supercomputing e.V. (https://www.gausscentre.eu) for funding this project by pr...     »