In response to the fourth AIAA CFD Drag Prediction Workshop, the NASA Common Research Model wing–body and wing–body–tail configurations are analyzed using the Reynolds-averaged Navier–Stokes flow solvers CFL3D and OVERFLOW. Two families of structured, overset grids are built. Grid Family 1 consists of a coarse (7.2 million), medium (16.9 million), fine (56.5 million), and extra-fine (189.4 million) mesh. Grid Family 2 is an extension of the first and includes a super-fine (714.2 million) and an ultra-fine (2.4 billion) mesh. The medium grid anchors both families with an established build process for accurate cruise drag prediction studies. This base mesh is coarsened and enhanced to form a set of parametrically equivalent grids that increase in size by a factor of roughly 3.4 from one level to the next denser level. Both CFL3D and OVERFLOW are run on Grid Family 1 using a consistent numerical approach. Additional OVERFLOW runs are made to study effects of differencing scheme and turbulence model on Grid Family 1 and to obtain results for Grid Family 2. All CFD results are post-processed using Richardson extrapolation, and approximate grid-converged values of drag are compared. The medium grid is also used to compute a trimmed drag polar for both codes.
Drag Prediction for the Common Research Model Using CFL3D and OVERFLOW
Journal of Aircraft ; 51 , 4 ; 1101-1117
2014-04-28
17 pages
Article (Journal)
Electronic Resource
English
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