A fast inverse design method based on direct surface transpiration concept

  • Jiri Blazek
Design Methods
Part of the Lecture Notes in Physics book series (LNP, volume 490)


An efficient inverse design method based on the direct surface transpiration concept has been presented. The results indicate its rapid convergence — after about 30 design iterations the target pressure is accurately matched. These are only 3 times more multigrid iterations than required for an analysis run. The method is also robust in the case of ill-posed pressure distribution. The design process of course does not converge, but the prescribed pressure is matched as close as physically possible. As an advantage, because the design part is separated from the flow solver, the present method can easily be implemented into a standard CFD code.


Pressure Coefficient AIAA Paper Transonic Flow Target Pressure Mach Number Distribution 
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6. References

  1. [1]
    Dulikravich, G.S.: Shape Inverse Design and Optimization for Three-Dimensional Aerodynamics. AIAA paper 95-0695, 1995.Google Scholar
  2. [2]
    Leonard, O.: Subsonic and Transonic Cascade Design. AGARD-R-780, pp. 7.1–7.18, 1990.Google Scholar
  3. [3]
    Leonard, O.; Van den Braembussche, R.A.: Design Method for Subsonic and Transonic Cascade with Prescribed Mach Number Distribution. ASME Paper 91-GT-18, 1991.Google Scholar
  4. [4]
    Wang, Z.; Dulikravich, G.S.: Inverse Shape Design of Turbomachinery Airfoils Using Navier-Stokes Equations. AIAA paper 95-0304, 1995.Google Scholar
  5. [5]
    Whittfield, D.L.; Janus, J.M.: Three-Dimensional Unsteady Euler Equations Solution Using Flux Vector Splitting. AIAA paper 84-1552, 1984.Google Scholar
  6. [6]
    Rieger, H.; Jameson, A.: Solution of Steady Three-Dimensional Compressible Euler and Navier-Stokes Equations by an Implicit LU Scheme. AIAA paper 88-0619, 1988.Google Scholar
  7. [7]
    Blazek, J.: Investigations of the Implicit LU-SSOR Scheme. DLR-FB 93-51, 1993.Google Scholar
  8. [8]
    Blazek, J.: A Multigrid LU-SSOR Scheme for the Solution of Hypersonic Flow Problems. AIAA paper 94-0062, 1994.Google Scholar
  9. [9]
    Jameson, A.; Schmidt, W.; Turkel, E.: Numerical Solutions of the Euler Equations by Finite Volume Methods Using Runge-Kutta Time-Stepping Schemes. AIAA paper 81-1259, 1981.Google Scholar
  10. [10]
    Van Leer, B.: Flux-Vector Splitting for the Euler Equations. Technical Report 82-30, ICASE, 1982.Google Scholar

Copyright information

© Springer-Verlag 1997

Authors and Affiliations

  • Jiri Blazek
    • 1
  1. 1.Fluid Dynamics & Combustion Dept.ABB Turbo Systems LtdBadenSwitzerland

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