Hybrid RANS/LES Simulation of a Supersonic Coaxial He/Air Jet Experiment at Various Turbulent Lewis Numbers

Conference paper
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design book series (NNFM, volume 137)


In this article, the unstructured, high order finite-volume CFD solver FLUSEPA, developed by Airbus Safran Launchers, is used to simulate a supersonic coaxial Helium/Air mixing experiment. The aim is to assess the ability of the code to accurately represent mixing in compressible flows and to create a reference case in order to test a future hybrid RANS/LES (HRL) model with variable turbulent Prandtl and Schmidt numbers. Both RANS and HRL simulations are performed and the impact of Lewis number on the results is studied. Fine and coarse meshes are used to see the influence of spatial resolution on modeled and resolved scales. General good agreement is obtained for both RANS and HRL simulations. Predictably, the choice of Lewis numbers has almost no impact on the time-averaged fields of the fine HRL simulation. Its role is more significant on the coarse mesh and the steady RANS simulations.



We would like to thank Professor Andrew D. Cutler for providing all data and additional details about the experiment.


  1. 1.
    Baurle, R.A., Edwards, J.R.: Hybrid reynolds-averaged/large eddy simulations of a coaxial supersonic freejet experiment. AIAA J. 48, 551–571 (2010)Google Scholar
  2. 2.
    Baurle, R.A.: Modeling of high-speed reacting flows: established practices and future challenges. AIAA 267 (2004)Google Scholar
  3. 3.
    Boussinesq, J.V.: Essai sur la théorie des eaux courantes. Mémoire des savants étrangers, Académie des sciences de Paris (1877)Google Scholar
  4. 4.
    Brenner, P.: Three dimensional aerodynamics with moving bodies applied to solid propellant. In: 27th Joint Propulsion Conference, Sacramento, USA (1991)Google Scholar
  5. 5.
    Brenner, P.: Simulation du mouvement relatif de corps soumis a un écoulement instationnaire par une méthode de chavauchement de maillage. In: AGARD Conference Proceedings 578: Progress and Challenges in CFD Methods and Algotithms, Seville, Spain (1995)Google Scholar
  6. 6.
    Brenner, P.: A conservative overlapover grid method to simulate tocket stage separation. In: 3rd Symposium on Overset Composite Grid and Solution Technology, Los Alamos (1996)Google Scholar
  7. 7.
    Brinckman, K.W., Calhoon Jr., W.H., Dash, S.M.: Scalar fluctuation modeling for high-speed aeropropulsive flows. AIAA J. 45, 1036–1046 (2007)Google Scholar
  8. 8.
    Catris, S., Aupoix, B.: Density corrections for turbulence models. Aerosp. Sci. Technol. 4, 1–11 (2000)Google Scholar
  9. 9.
    Cocks, P.: Large eddy simulation of supersonic combustion with application to scramjet engines. Ph.D. thesis, University of Cambridge (2011)Google Scholar
  10. 10.
    Cutler, A.D., Diskin, G.S., Drummond, J.P., White, J.A.: Supersonic coaxial jet experiment for computational fluid dynamics code validation. AIAA J. 44, 585–592 (2006)Google Scholar
  11. 11.
    Monge, G.: Géométrie Descriptive. Paris, Baudouin, Imprimeur du Corps lgislatif et de linstitut national, AN VII (1799)Google Scholar
  12. 12.
    Pont, G.: Self adaptive turbulence models for unsteady compressible flows. Ph.D. Arts et Méters ParisTech, Airbus Defense & Space (2015)Google Scholar
  13. 13.
    Strelets, M.: Detached eddy simulation of massively separated flows. In: AIAA, 39th Aerospace Sciences Meeting and Exhibit, Reno, NV (2001)Google Scholar
  14. 14.
    Xiao, X., Hassan, H.A., Baurle, R.A.: Modeling scramjet flows with variable turbulent prandtl and schmidt numbers. AIAA J. 45, 1415–1423 (2007)Google Scholar

Copyright information

© Springer International Publishing AG 2018

Authors and Affiliations

  1. 1.ENSAM DynFluidParisFrance
  2. 2.Airbus Safran LaunchersLes MureauxFrance

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