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Shock Control Bumps on Flexible and Trimmed Transport Aircraft in Transonic Flow

  • Benedikt König
  • Martin Pätzold
  • Thorsten Lutz
  • Ewald Krämer
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 96)

Abstract

Shock control bumps are a means to reduce wave drag that occurs at the upper limit of civil transport aircrafts flight envelope. An SCB was optimized for and applied to the rigid wing-body DLR F11 model. The effect of the SCB on the trim drag of the F11 configuration with an attached horizontal tail plane was investigated. Flexibility of the wing-body model was considered and the influence of aeroelasticity on the SCB performance was examined. RANS simulations with the DLR FLOWer code showed, that both the influence of trimming as well as of aeroelasticity is negligible for SCB design.

Keywords

Drag Reduction Transonic Flow Pitching Moment Total Pressure Loss Wave Drag 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. [1]
    N. Kroll, C. C. Rossow, D. Schwamborn, K. Becker and G. Heller: MEGAFLOW — a Numerical Flow Simulation Tool for Transport Aircraft Design. In: Proceed-ings of the 23rd International Congress of Aeronautical Sciences, ICAS, 2002. Toronto.Google Scholar
  2. [2]
    M. Kutzbach, T. Lutz and S. Wagner: Investigations on Shock Control Bumps for Infinite Swept Wings. In: 2nd AIAA Flow Control Conference, Portland, Oregon, USA, June 28–July 1, 2004.Google Scholar
  3. [3]
    T. Lutz, A. Sominerer and S. Wagner: Parallel Numerical Optimisation of Adap-tive Transonic Airfoils. In: Fluid Mechanics and its Applications, Vol. 73, Kluwer Academic Publishers, 2003. Symposium Transsonicum IV, Göttingen, Germany, September 2–6, 2002.Google Scholar
  4. [4]
    T. Mauermann: The FEMSPLINE-Method for Connecting Condensed Struc-tural Models and Aerodynamic Models. Tech. Rep., Airbus Deutschland GmbH, Loads & Aeroelastics EGLG31, 2005.Google Scholar
  5. [5]
    M. Michael: Personal Communictation on Structural Models of Free Flying Air-craft. unpublished, 2006. Institut für Flugmechanik und Regelungstechnik, Universität Stuttgart.Google Scholar
  6. [6]
    A. Sommerer: Numerische Optimierung adaptiver transsonischer Profile. Dis-sertation, Institut für Aerodynamik und Gasdynamik, Universität Stuttgart, 2005.Google Scholar
  7. [7]
    E. Stanewsky, J. Delery, J. Fulker and P. de Matteis: EUROSROCK II: Drag Reduction by Shock Boundary Layer Control. Notes on numerical fluid mechan-ics and multidisciplinary design, Vol. 80. Springer, 2002.Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2007

Authors and Affiliations

  • Benedikt König
    • 1
  • Martin Pätzold
    • 1
  • Thorsten Lutz
    • 1
  • Ewald Krämer
    • 1
  1. 1.Institut für Aerodynamik und Gasdynamik (IAG)Universität StuttgartStuttgartGermany

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