Mesh Effects on Flow Solutions for a 2D Multi-Element Airfoil Using Structured Overset Methods

Speaker: Andrew Chuen, Computational Aerosciencies Branch, NASA Advanced Supercomputing Division
July 23, 2020

Presentation

Abstract

Current best-practices for mesh generation in a structured overset framework are evaluated to determine their effects on the accuracy and convergence of the flow solution on a two-dimensional sectional cut of the High-Lift Common Research Model (HLCRM) wing. The trends and sensitivities of mesh parameter variations and the characteristics of a best practice mesh are established by correlating with force and moment coefficients computed from the flow solutions. Additional investigations in “C” versus “O” mesh topologies and resolution of various flow features, such as shear layers and wakes, are also considered. A grid convergence study is used to evaluate the accuracy of the final best-practice mesh. A mesh adaption study using the OVERFLOW flow solver is also performed to determine the minimum mesh quality needed in order for feature-based adaption to reach an accurate flow solution. Recent investigations also consider the effect of prescribed leading edge resolution on the mesh adaption results.

Biography

Andrew Chuen is a NASA Pathways Intern in the Computational Aerosciencies Branch of the NASA Advanced Supercomputing Division at NASA's Ames Research Center. He is also currently a Ph.D. student under the advisement of Professor Mohamed Hafez in the Mechanical and Aerospace Engineering Department at the University of California, Davis. Prior to his doctoral studies, Andrew received his M.S. and B.S. degrees in Mechanical and Aerospace engineering at UC Davis. In his M.S. thesis, Andrew investigated non-uniqueness in two-dimensional compressible flows.

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