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A mixed explicit-implicit antidiffusive method of navier-stokes equations for supersonic and hypersonic separated flows

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Abstract

The supersonic and hypersonic, laminar and turbulent viscous separated flows over two and three-dimensional compression corners are solved by the antidissipative explicit-implicit difference scheme presented in this paper. The results obtained show that a high accuracy has been achieved by this method and the time needed for computation is greatly reduced.

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References

  1. Zhang H.X., L.S. Lu, Z.C. Yu and Z.K. Ma,Acta Mechanica Sinica, Vol. 7, No. 4, (1981).

  2. Zhang H.X.,Turbulence modelling, Chinese Aerodynamics Research and Development Center Report, (1981).

  3. Hung C.M. and R.W. MacCormack, AIAA Paper 75-2, (1975).

  4. Carter, J.E., NASA TR R-385, (1972).

  5. Shang J.S. and W.L. Hankey, Jr., AIAA Paper 75-3, (1975).

  6. Holden, M.S. and J.R. Mosell, CALSPAN Report, No. AF-2410-A-1, (1969).

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Authors and Affiliations

  1. Chinese Aerodynamic Research and Development Center, China

    Zhang Han-xin, Lu Lin-sheng, Yu Ze-chu & Ma Zhan-kui

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  1. Zhang Han-xin
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  2. Lu Lin-sheng
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  3. Yu Ze-chu
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  4. Ma Zhan-kui
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Han-xin, Z., Lin-sheng, L., Ze-chu, Y. et al. A mixed explicit-implicit antidiffusive method of navier-stokes equations for supersonic and hypersonic separated flows. Appl Math Mech 4, 55–68 (1983). https://doi.org/10.1007/BF01896713

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  • DOI: https://doi.org/10.1007/BF01896713

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