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Computation of turbulent separated nozzle flows

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Shock Waves

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Abstract

The computationally challenging case of an over-expanded nozzle flow involving shock induced boundary layer separation is examined in this paper. Comparative studies using a base line two-equation k − ω turbulence model with and without taking into account non-equilibrium effects are made. The additional equation (the lag equation) to model nonequilibrium effect for the eddy viscosity in the separated flow region, significantly improves predictions of shock induced separated flows in exhaust nozzle.

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References

  1. S.C. Asbury, C.L. Gunther, C.A. Hunter: A passive cavity concept for improving the off-design performance of fixed-geometry exhaust nozzles. AIA A 96-2541 (1996)

    Google Scholar 

  2. C.A. Hunter: An Experimental Analysis of Passive Shock-boundary Layer Interaction Control for Improving the Off-design Performance of Jet Exhaust Nozzles. M.S. Thesis, The George Washington University JIAFS. (1993)

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  3. C.A. Hunter: Experimental, theoretical, and computational investigation of separated nozzle flows. AIAA 98-3107 (1998)

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  4. J.R. Carlson: A nozzle internal performance prediction method. NASA Technical Paper 3221 (1992)

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  5. M.E. Olsen, T.J. Coakley: The lag model, a turbulence model for non equilibrium flows. AIAA 2001-2564 (2001)

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  6. Q. Xiao, H.M. Tsai, F. Liu: Computation of transonic diffuser flows by a lagged k — ω turbulence model. Journal of Propulsion and Power 19(3), (2003)

    Google Scholar 

  7. F. Liu, S.H. Ji: Unsteady flow calculations with a multigrid Navier-Stokes method. AIAA Journal 34(10), 2047 (1996)

    Article  ADS  Google Scholar 

  8. A. Jameson: Time dependent calculations using multigrid, with applications to unsteady flows past airfoils and wings. AIAA Paper 91-1596 (1991)

    Google Scholar 

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Author information

Authors and Affiliations

  1. Temasek Laboratories, National University of Singapore, 10 Kent Ridge Crescent, Singapore, 119260, Singapore

    Q. Xiao & H. M. Tsai

Authors
  1. Q. Xiao
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  2. H. M. Tsai
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Editor information

Editors and Affiliations

  1. Key Laboratory of High-Temperature Gas Dynamics Institute of Mechanics, Chinese Academy of Sciences, 15 Bei Si Huan Xi Rd., Beijing, 100080, P.R. China

    Z. Jiang

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© 2005 Tsinghua University Press and Springer-Verlag Berlin Heidelberg

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Xiao, Q., Tsai, H.M. (2005). Computation of turbulent separated nozzle flows. In: Jiang, Z. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-27009-6_172

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  • DOI: https://doi.org/10.1007/978-3-540-27009-6_172

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  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-540-22497-6

  • Online ISBN: 978-3-540-27009-6

  • eBook Packages: Physics and AstronomyPhysics and Astronomy (R0)

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