The current 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 SA model has been extended by incorporating the existing crossflow model, which was originally developed to be coupled with the 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 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.
Spalart–Allmaras with Crossflow Transition Model Using Hamiltonian–Strand Approach
Journal of Aircraft ; 56 , 3 ; 1040-1055
2019-01-14
16 pages
Article (Journal)
Electronic Resource
English
Combustion Analysis Using Roe's Scheme and the Spalart-Allmaras Model
Online Contents | 2009
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