TY - GEN
T1 - Comparison of fixed andadaptive unstructured grid results for drag prediction workshop 6
AU - Michal, Todd
AU - Babcock, Deric
AU - Kamenetskiy, Dmitry
AU - Krakos, Joshua
AU - Mani, Mortaza
AU - Glasby, Ryan
AU - Erwin, Taylor
AU - Stefanski, Douglas L.
N1 - Publisher Copyright:
© 2017 by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2017
Y1 - 2017
N2 - Fixed and adapted grid solutions on the NASA Common Research Model (CRM) in wing-body (WB) and wing-body-nacelle-pylon (WBNP) configurations are compared for three Reynolds Averaged Navier-Stokes (RANS) flow solvers. The flow solvers were run on a sequence of fixed unstructured grids built for the 6th AIAA CFD Drag Prediction Workshop (DPW-6) and compared with solutions generated on solution adaptive grids. The fixed and adaptive mesh generation processes and resulting grids and solutions are presented and discussed. Both approaches achieve asymptotic grid convergence of less than 2 counts of drag. The fixed grid approach is based on gridding guidelines developed over many years of CFD application experience on similar applications and required an expert user several weeks of effort to develop a grid family conforming to the guidelines. In contrast, the adaptive grid approach is automatic, relying on an estimate of solution discretization error to guide the grid construction.
AB - Fixed and adapted grid solutions on the NASA Common Research Model (CRM) in wing-body (WB) and wing-body-nacelle-pylon (WBNP) configurations are compared for three Reynolds Averaged Navier-Stokes (RANS) flow solvers. The flow solvers were run on a sequence of fixed unstructured grids built for the 6th AIAA CFD Drag Prediction Workshop (DPW-6) and compared with solutions generated on solution adaptive grids. The fixed and adaptive mesh generation processes and resulting grids and solutions are presented and discussed. Both approaches achieve asymptotic grid convergence of less than 2 counts of drag. The fixed grid approach is based on gridding guidelines developed over many years of CFD application experience on similar applications and required an expert user several weeks of effort to develop a grid family conforming to the guidelines. In contrast, the adaptive grid approach is automatic, relying on an estimate of solution discretization error to guide the grid construction.
UR - http://www.scopus.com/inward/record.url?scp=85017129922&partnerID=8YFLogxK
U2 - 10.2514/6.2017-0961
DO - 10.2514/6.2017-0961
M3 - Conference contribution
AN - SCOPUS:85017129922
T3 - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 55th AIAA Aerospace Sciences Meeting
Y2 - 9 January 2017 through 13 January 2017
ER -