Volume 26 Issue 6
Jun.  2000
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LI Jin, ZHU Zi-qiang, WU Zong-cheng, et al. Euler Solution of a 3D WingBody Configuration with Aileron[J]. Journal of Beijing University of Aeronautics and Astronautics, 2000, 26(6): 680-683. (in Chinese)
Citation: LI Jin, ZHU Zi-qiang, WU Zong-cheng, et al. Euler Solution of a 3D WingBody Configuration with Aileron[J]. Journal of Beijing University of Aeronautics and Astronautics, 2000, 26(6): 680-683. (in Chinese)

Euler Solution of a 3D WingBody Configuration with Aileron

  • Received Date: 31 May 1999
  • Publish Date: 30 Jun 2000
  • A Euler method for solving the flow around a wing-body configuration with deflection of control surface (aileron) is presented. Using the combination of patched grid and domain decomposition techniques, the complex flow around this kind of configuration is effectively solved. An internal coupling condition is given to make the conservation of flux satisfied. In the computation Van Leer-s scheme is used to discretize the inviscid flux terms and a new Limiter function is constructed to realize TVD character. Numerical results show that present method is an effective one for solving the flow around wing-body configuration with control surface deflection .

     

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  • [1] Li Jin, Zhu Ziqiang, Chen Zemin,et al. The Euler solution of a 3D wing with aileron. Proceedings of the 3rd international conference on fluid mechanics. Beijing:Beijing Institute of Technology Press, 1998, 286~294. [2]Pulliam T H, Steger J L. Recent improvements in efficiency, accuracy and convergence for implicit factorization algorithms. AIAA 85-0360, 1985. [3]Van Leer B. Flux-Vector Splitting for the Euler Equations[J]. Lect Notes in Physics, 1982,170:507~512. [4]Van Leer B. Towards the ultimate conservative difference scheme V:A second-order sequel to Gudonov-s method[J]. J of Comp Physics, 1979, 32:101~136. [5]Li Jin, Chen Zemin, Zhu Ziqiang. New approach to the limiter functions. J of Comp Math, 1999,17(3):41~58. [6]Benek J A, Buning P G, Steger J L. A 3-D chimera grid embedding technique. AIAA 85-1523, 1985. [7]Hess R W, Cazier F W Jr, Wynne E C. Steady and unsteady transonic pressure measurements on a clipped Delta wing for pitching and control-surface oscillations. NASA TP 2549, 1986. [8]Obayashi S, Guruswavmy G P. Navier-Stokes computations for oscillating control surfaces. AIAA 92-4431, 1992.
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