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Numerical Simulations of Artificial Disturbance Influence on a High Lift Airfoil

In: High Performance Computing in Science and Engineering ' 17

Author

Listed:
  • Katharina Wawrzinek

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics (IAG))

  • Thorsten Lutz

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics (IAG))

  • Ewald Krämer

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics (IAG))

Abstract

Numerical simulation results of the DLR-F15 high lift airfoil with statically and dynamically disturbed inflow conditions are presented and analysed. The two-dimensionally extruded high-lift airfoil, consisting of main element and flap, is exposed to the influence of a static tip vortex in order to generate a three-dimensional inflow condition. In a second step the static distortion is superimposed by an additional, artificial and dynamic gust. The set-up is a wind tunnel test section, where a pitching airfoil, which serves as a gust generator, and a finite wing, which serves as a vortex generator, are located upstream of the high lift airfoil. Unsteady RANS simulations with the inflow Mach number M ∞ = 0.15 and Reynolds number Re = 2.0 million were performed. The high lift airfoil angle of attack is α = 0∘. The results give an insight into the different emerging effects and the reaction of the high lift airfoil.

Suggested Citation

  • Katharina Wawrzinek & Thorsten Lutz & Ewald Krämer, 2018. "Numerical Simulations of Artificial Disturbance Influence on a High Lift Airfoil," Springer Books, in: Wolfgang E. Nagel & Dietmar H. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering ' 17, pages 323-337, Springer.
    • Handle: RePEc:spr:sprchp:978-3-319-68394-2_19
    DOI: 10.1007/978-3-319-68394-2_19
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