This paper documents a comparison of overset grid and grid deformation schemes applied to flapped and non-flapped NACA airfoil configurations in order to determine the relative accuracy and computational efficiency of each method. This study is part of a larger effort to use computational fluid dynamics to perform moving control surface calculations. Three different cases, using both overset and deformed grids, are considered, including: a) lift and moment comparison of a quasi-steady, non-flapped 0012 airfoil, b) lift and moment comparison of a dynamically pitching non-flapped 0012 airfoil, and c) lift comparison of a dynamic pitching and oscillating flapped 0012 airfoil. These results are compared to experimental data from various sources. Two flow solvers of common lineage were used for the computations: Cobalt for overset and rigid mesh motion and AVUS for the deformable mesh motion. All of the methods produced nominally similar results. As expected, the rigid mesh technique required the least amount of computational resources, while the deformable mesh technique required the greatest amount of computational resources due to its serial implementation. However, in the end, it is difficult to recommend one method over another as the application of each method may be dependent on the project being solved.


Aerospace Engineering

Publisher statement

This article is in the public domain. Published by American Institute of Aeronautics and Astronautics.



URL: http://digitalcommons.calpoly.edu/aero_fac/48