Advertisement

Application of the Adjoint Technique with the Optimization Framework Synaps Pointer Pro

  • Joël Brezillon
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 89)

Summary

The present paper aims at describing the potential of the adjoint technique for aerodynamic shape optimization. After a brief description of the aerodynamic optimization process developed at DLR, specific requirements for an optimization framework combined with the adjoint technique are introduced. The drag reduction by constant lift and pitching moment for the RAE 2822 airfoil in transonic flow is then presented as validation case. An extension to multi-point optimization demonstrates the capability of the methodology to solve more complex problems. At the end, the body optimization and the wing optimization of a supersonic commercial aircraft confirm the flexibility of the framework and the efficiency of the adjoint technique.

Keywords

Pitching Moment Wing Section Body Optimization Mach Number Distribution Adjoint Approach 
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.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    Axmann J.K., Hadenfeld M. and Frommann O.: “Parallel Numerical Airplane Wing Design”. New Results in Numerical and Experimental Fluid Mechanics: Contributions to the 10th AG STAB/DGLR Symposium”, Vieweg Verlag, 1997.Google Scholar
  2. 2.
    Enoksson O. and Weinerfelt P.: “Numerical Methods for Aerodynamic Optimisation”. 8th International Symposium on Comp. Fluid Dynamics, Sep. 5–10 1999, Bremen, Germany.Google Scholar
  3. 3.
    Frommann O.: “SynapsPointer Pro V2.50”, Synaps Ingenieur-Gesellschaft mbH, Bremen, Germany 2002. AIAA-98-2730, 1998.Google Scholar
  4. 4.
    Gauger N. R.: “Aerodynamic Shape Optimization using Adjoint Euler Equations”. Proceeding of the GAMM Workshop ‘Discrete Modelling and Discrete Algorithms in Continuum Mechanics’, pp 87–96, Logos Verlag Berlin, 2001Google Scholar
  5. 5.
    Gauger N. R. and Brezillon J: “The Continuous Adjoint Approach in Aerodynamic Shape Optimization”. Present Notes on Numerical Fluid MechanicsGoogle Scholar
  6. 6.
    Hicks R.M. and Henne P.A.: “Wing design by numerical optimization”. Journal of Aircraft, Vol. 15, pp. 407–412, 1978.CrossRefGoogle Scholar
  7. 7.
    Lovell D.A.: “Aerodynamic Research to Support a Second Generation Supersonic Transport Aircraft-the EUROSUP Project”. Eccomas 98, 1998Google Scholar
  8. 8.
    Lovell D.A.: “European Research of Wave and Lift Dependant Drag for Supersonic Transport Aircraft”. AIAA Paper No. 99-3100, 1999Google Scholar
  9. 9.
    Selmin, V.: “Multi-point aerodynamic shape optimization: The AEROSHAPE project”. Proceedings of ECCOMAS, Barcelona, Spain, 2000.Google Scholar
  10. 10.
    Whitcomb R.T., Sevier J.R.: “A Supersonic Area Rule and an Application to the Design of a Wing-Body combination with high Lift-Drag Ratios”. NASA TR R-72, 1960Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • Joël Brezillon
    • 1
  1. 1.DLRInstitute of Aerodynamics and Flow TechnologyBraunschweig

Personalised recommendations