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- W3006586525 abstract "Computational Fluid Dynamics (CFD) simulations are frequently used in the aerospaceindustry to help reduce development times by cutting down on the need of extensive windtunnel campaigns. However, although design-point aerodynamics are well predicted, edge ofthe envelope scenarios dominated by non-linear fluid phenomena can lead to uncertainties inthe accuracy of the results produced.This work addresses the use of Reynolds-averaged Navier-Stokes (RANS) based simulationsin the prediction of unsteady shock-buffet phenomenon. Three studies are conducted: a 2Dvalidation study, a 3D validation study, and the pinnacle of this work which presents a novelshock-buffet prediction on an industrially-relevant aircraft confguration.Two dimensional shock-buffet predictions are presented as a confrmation of previous available knowledge. The dependency on turbulence modelling approaches is evident, with newresults showing that the full Reynolds Stress Model (RSM) is a more appropriate closure tothe RANS equations than other typically used eddy-viscosity-based models. However, thisimplies additional computational costs (due to increased number of equations solved), andinherited challenges associated with solver stability.RANS-based simulations are then applied to a 3D confguration: the NASA CommonResearch Model (CRM) wing-body test case. Complementary results to the AIAA CFD DragPrediction Workshop are produced. Novel results, outside the Drag Prediction Workshopenvelope, investigate the development and expansion of the shock-induced boundary layerseparation on the NASA CRM wing, however the steady RANS approach fails to accuratelypredict this due to unsteady effects which are not accounted for.Unsteady simulations in the shock-buffet regime of the wing-body NASA CRM are thenpresented as the main novel contribution of this work. The complexity of the phenomenon isrevealed by unsteady shock oscillations coupled with shock-induced separation and vortexshedding. The presence of shock-buffet cells is detected and helps understand shock dynamics.A frequency analysis reveals the presence of multiple peak frequencies. A qualitativecomparison with experimental observation show similarity in the physics produced. Finally,to further investigate the shock-buffet phenomenon, the effects of changing the Reynoldsnumber are presented.Through industrial relevance, the current work can lead to decision making in the developmentof the future generation of aircraft." @default.
- W3006586525 created "2020-02-24" @default.
- W3006586525 creator A5016350374 @default.
- W3006586525 date "2019-09-01" @default.
- W3006586525 modified "2023-09-26" @default.
- W3006586525 title "Numerical prediction and characterization of shock-buffet in transport aircraft" @default.
- W3006586525 hasPublicationYear "2019" @default.
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