The feasibility of laminar flow control technology for future wing is bound to the development of a leading edge high-lift system that complies with the requirements on smooth surfaces to enable maintaining the laminar boundary layer flow, such as a Krueger flap. Although in principle the aerodynamic performance of a Krueger flap is known, the unsteady behaviour of the flow during deployment and retraction is completely unknown. This is as even more important as during deployment the Krueger flap is exposed to highly unfavourable positions perpendicular to the flow. To mitigate the risk of unfavourable aircraft behaviour, it is therefore expected that a Krueger flap has to be deflected significantly fast and may trigger unsteady aerodynamic effects. Within the European H2020 project UHURA (Unsteady High-Lift Aerodynamics—Unsteady RANS Validation), currently a wind tunnel test is conducted incorporating the vented foldable bull nose Krueger flap. A wind tunnel model based on the DLR-F15 airfoil has been designed and manufactured that features a part span and a full span Krueger device, which can be actuated at high deflection rates up to 360°/s. First wind tunnel tests have been conducted at the ONERA L1 wind tunnel in Lille in October 2020. The tests included the measurements of internal forces, steady and unsteady pressures, as well as phase-locked Particle Image Velocimetry (PIV) to achieve high quality validation data for comparison with numerical methods.
- High-lift system
- Krueger flap
- Unsteady flow
- Wind tunnel test
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Boeing Commercial Aircraft Group (1999) High Reynolds number hybrid laminar flow control (HLFC) Flight Experiment; Part II. Aerodynamic Design. NASA-CR-209324:65–73
Strüber H, Wild J (2014) Aerodynamic design of a high-lift system compatible with a natural laminar flow wing within the DeSiReH Project. Paper presented at the 29th congress of the international council of the aeronautical sciences, St Petersburg, Russia, 7–12 Sept 2014. Paper-ID ICAS 2014–0300
Wild J (2013) Mach and reynolds number dependencies of the stall behavior of high-lift wing sections. J Aircr 50(4):1202–1216. https://doi.org/10.2514/1.C032138
Ciobaca V, Dandois J (2017) High reynolds number high-lift airfoil testing with flow control. Paper presented at the 35th AIAA applied aerodynamics conference, June 5–9 2017. Paper-ID AIAA 2017–3245. https://doi.org/10.2514/6.2017-3245
The project leading to this presentation has received funding from the European Union’s Horizon 2020 Research and Innovation Framework Programme under the grant agreement No 769088.
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Wild, J., Schmidt, M., Vervliet, A., Tanguy, G. (2022). A 2D Validation Experiment for Dynamic High-Lift System Aerodynamics. In: Knoerzer, D., Periaux, J., Tuovinen, T. (eds) Advances in Computational Methods and Technologies in Aeronautics and Industry. Computational Methods in Applied Sciences, vol 57. Springer, Cham. https://doi.org/10.1007/978-3-031-12019-0_3
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