The current γ R e θ t ¯ Spalart–Allmaras (SA) laminar–turbulent transition model is evaluated through the representative two- and three-dimensional test cases within the line-based Hamiltonian–Strand grid flow solver. To consider crossflow instability on transition onset, the baseline γ R e θ t ¯ SA model has been extended by incorporating the existing crossflow model, which was originally developed to be coupled with the γ R e θ t ¯ model. For the extension, a simple modification is only required on the baseline transition model, and the extended model has been used with both structured and unstructured/strand grid types using the present flow solver. The extended transition model is applied on the representative test cases where crossflow is dominant, such as the NLF(2)-0415 wing, ONERA M6 swept wing, inclined prolate spheroid, and a challenging sickle wing. By comparing the results with the baseline γ R e θ t ¯ SA model, predictive results are observed through the validation of test cases. The limitations of the extended model are also found through the sickle-wing test.


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    Title :

    γ R e θ t ¯ Spalart–Allmaras with Crossflow Transition Model Using Hamiltonian–Strand Approach


    Contributors:

    Published in:

    Journal of Aircraft ; 56 , 3 ; 1040-1055


    Publication date :

    2019-01-14


    Size :

    16 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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