Unsteady simulations of the NASA Common Research Model using a new transonic lattice Boltzmann method are conducted for the Sixth AIAA CFD Drag Prediction Workshop. The context for the development of this unique new method is briefly described. The results of a grid convergence study are presented and discussed, and it is shown that the numerical method is capable of accurately predicting incremental drag changes. The occurrence of unsteady flow at higher angles of attack during an alpha sweep for the model including static aeroelastic wing deformations is discussed. Buffet is already shown to start locally on the wing for angles of attack considered for the workshop. Additional simulations for higher angles, deep into the buffet range and close to the high-speed stall of the model, are also shown and highlight the method’s capability to handle highly unsteady flows with massive turbulent separations.
Exa PowerFLOW Simulations for the Sixth AIAA Drag Prediction Workshop
Journal of Aircraft ; 55 , 4 ; 1482-1490
2018-07-01
Conference paper , Article (Journal)
Electronic Resource
English
Exa PowerFLOW Simulations for the Sixth AIAA Drag Prediction Workshop (AIAA 2017-0963)
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