TY - GEN
T1 - Comparison of Full-Field and Integrated CFD Convergence Based on Richardson Extrapolation
AU - Weinmeister, Justin
AU - Sanjaya, Devina P.
N1 - Publisher Copyright:
© 2024, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2024
Y1 - 2024
N2 - This work investigated the usefulness of Richardson extrapolation–based discretization error estimates across all points in a solution field to produce a spatial convergence field for a computational fluid dynamics (CFD) simulation. The presented work used previously developed methods for Richardson extrapolation to compute the convergence orders of a CFD simulation at all points of the base (coarsest) mesh solution. Three test cases of increasing complexity were considered: Poiseuille flow, incompressible flow around a sharp corner, and transonic flow over an RAE 2822 airfoil. These test cases highlighted the potential of the proposed method to identify error sources and their relation to the model system-response-quantity convergence orders. However, these test cases also revealed the immaturity of the proposed method stemming from the unreliability of computing observed convergence orders at single points. Nonetheless, the test cases highlighted that the observed convergence orders allow for a more accurate diagnosis of constructive and destructive error transport than mesh pair error estimates. In the long run, the proposed method can be a tool for developing efficient and advanced error management strategies like adaptive mesh refinement.
AB - This work investigated the usefulness of Richardson extrapolation–based discretization error estimates across all points in a solution field to produce a spatial convergence field for a computational fluid dynamics (CFD) simulation. The presented work used previously developed methods for Richardson extrapolation to compute the convergence orders of a CFD simulation at all points of the base (coarsest) mesh solution. Three test cases of increasing complexity were considered: Poiseuille flow, incompressible flow around a sharp corner, and transonic flow over an RAE 2822 airfoil. These test cases highlighted the potential of the proposed method to identify error sources and their relation to the model system-response-quantity convergence orders. However, these test cases also revealed the immaturity of the proposed method stemming from the unreliability of computing observed convergence orders at single points. Nonetheless, the test cases highlighted that the observed convergence orders allow for a more accurate diagnosis of constructive and destructive error transport than mesh pair error estimates. In the long run, the proposed method can be a tool for developing efficient and advanced error management strategies like adaptive mesh refinement.
UR - http://www.scopus.com/inward/record.url?scp=85204209920&partnerID=8YFLogxK
U2 - 10.2514/6.2024-4470
DO - 10.2514/6.2024-4470
M3 - Conference contribution
AN - SCOPUS:85204209920
SN - 9781624107160
T3 - AIAA Aviation Forum and ASCEND, 2024
BT - AIAA Aviation Forum and ASCEND, 2024
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation Forum and ASCEND, 2024
Y2 - 29 July 2024 through 2 August 2024
ER -