DPW-6: Drag Analyses and Increments Using Different Geometries of the Common Research Model Airliner
Résumé
This paper describes the CFD studies carried out at ONERA in the framework of the Sixth AIAA Drag Prediction Workshop. Different configurations of the well-known Common Research Model have been used to perform drag analyses and increment assessments. The structured overset grids provided by The Boeing Company to the DPW community have been preprocessed with the in-house software Cassiopée: CGNS conversion, cell blanking, and overlapping issues have been handled before running these grids with the RANS solver elsA and the far-field code ffd72. Contrary to the original CRM configuration used in DPW-5, the wing shape is now based on wind-tunnel aeroelastic measurements: through a grid convergence process, a four-count drag increment between new and former wing–body geometries has been quantified, which is very consistent with previous ONERA results. Then, a CRM configuration including a throughflow nacelle–pylon installation has been computed: the corresponding drag increment of about 22 counts is in very close agreement with the NASA experimental data. Finally, horizontal and vertical tails have been added to the wing–body–nacelle–pylon geometry so that the aerodynamic performance of such a complete cruise configuration can be assessed. Numerical considerations involving the SA-QCR2000 turbulence model are highlighted.
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