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Volume 29 Issue 3
Mar.  2003
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Journal of Beijing University of Aeronautics and Astronautics  > 2003  >  29(3): 269-272.
Sun Ruozi, Hua Jun. Modification of Transonic Wing Design Method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(3): 269-272. (in Chinese)
Citation: Sun Ruozi, Hua Jun. Modification of Transonic Wing Design Method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(3): 269-272. (in Chinese)
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Modification of Transonic Wing Design Method

  • Dept. of Flight Vehicle Design and Applied Mechanics, Beijing University of Aeronautics and Astronautics

  • Received Date: 22 Oct 2001
  • Publish Date: 31 Mar 2003
    Abstract
  • The residual-correction design method for transonic wings with prescribed pressure distribution developed by Takanashi was modified. In order to guarantee the convergence of the design in supersonic flow, Takanashi method could be modified by introducing some upwind based operator to the governing equation in hyperbolic parts. Results of the redesign of a wing indicate that the improved method can overcome the convergence problem of the original method in supersonic region and then is more practical in engineering application.

     

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    • References(1)
  • [1] Takanashi S. An iterative procedure for three-dimensional transonic wing design by the integral equation method . AIAA-84-2155,1984 [2] 华 俊. 跨应速翼型和机翼的设计研究 . 西安:西北工业大学飞机系, 1989 Hua J. Design research for transonic airfoils and wing . Xian:Aircraft Department, Northwestern Polytechnical University, 1989(in Chinese) [3] Hua J, Zhang Z Y. Transonic wing design for transport aircraft . ICAS-90-3.7.4,1990 [4] Bartelheimer W. Design of transonic airfoils and wings based on the solution of the Euler/Navier-Stokes equation . Germany:German Aerospace Center, 1994
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