Abstract
The wing of an active high lift aircraft configuration with an UHBR engine is structurally sized. The FEA details droop nose and flaps and uses loads from 3D CFD RANS simulations for the fully stressed design. The sizing yields a comparable skin thickness distribution compared to a similar wing configuration with a Turboprop engine. The differences in mass result mainly from the relatively high UHBR engine weight and the higher sweep angle. Furthermore the steady aeroelastic equilibrium is computed with a partitioned approach for the landing configuration at optimal circulation control. Flow separation is initiated at the end of the unprotected leading edge, propagating to the outboard main wing and aileron. The effect of the wing elasticity onto the aerodynamics is negligible due to the high stiffness of the UHBR configuration.
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Acknowledgements
The authors gratefully acknowledge the funding as part of the Coordinated Research Centre 880 provided by the German Research Foundation (Deutsche Forschungsgemeinschaft-DFG).
The computations were performed with resources provided by the North-German Supercomputing Alliance (HLRN).
The DLR-TAU computations have been set up with the help of Dennis Keller from Institute of Aerodynamics and Flow Technology, German Aerospace Center, Brunswick.
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Runge, F., Sommerwerk, K., Rohdenburg, M., Haupt, M.C. (2021). Design of Active High Lift Wing Configurations Via Fluid-Structure Interaction Simulation. In: Radespiel, R., Semaan, R. (eds) Fundamentals of High Lift for Future Civil Aircraft. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 145. Springer, Cham. https://doi.org/10.1007/978-3-030-52429-6_13
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