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The computation of transonic airfoil and wing design

  • Z. Q. Zhu
  • Z. X. Xia
  • L. Y. Wu
Part of the Acta Mechanica book series (ACTA MECH.SUPP., volume 4)

Summary

An inverse computational method for transonic airfoil and wing design is presented. Improvements aimed at increasing abilities of the method and computational efficiency have been taken. For example, a Riegels type leading edge correction is introduced. An artificial viscosity term is added to the integral equation method and a smoothing-relaxation procedure is proposed. In 2D transonic flow case, a regularity condition in closed form to be satisfied by a target pressure distribution is used. A few given design results illustrate that the present method is an efficient tool for transonic airfoil and wing design.

Keywords

Pressure Distribution Integral Equation Method Artificial Viscosity Aerodynamic Design Wing Design 
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

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Copyright information

© Springer-Verlag 1994

Authors and Affiliations

  • Z. Q. Zhu
    • 1
  • Z. X. Xia
    • 1
  • L. Y. Wu
    • 1
  1. 1.Institute of Fluid MechanicsBeijing University of Aeronautics and AstronauticsBeijingPeople’s Republic of China

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