Purpose: To estimate maximum and post-stall performance of a flat, thin wing.
This page details 2D Navier-Stokes simulations on flat plate wings. A 2D simulation would return upper bounds on performance, as the effects of 3D are typically detrimental to performance (tip vortices, span-wise flow, etc.).
First, some pictures of the flow field.
This page details 2D Navier-Stokes simulations on flat plate wings. A 2D simulation would return upper bounds on performance, as the effects of 3D are typically detrimental to performance (tip vortices, span-wise flow, etc.).
First, some pictures of the flow field.
The plots below show the results for a Reynolds number of 1.2 million. The numbers in the legend titles ('75', '150', and '300') denote the number of computational cells (evenly spaced) on the wing surface. As the plots below show, the results at higher angles of attack are grid converged, while angles around 5 degrees or lower show different behavior between the two resolutions.
The mesh used for the 150-chord-cell runs are shown below.
The solver used was simpleFoam (a steady-state solver) with second-order spatial discretization accuracy. More details can be found on my github page (lordvon) under the Gmsh/Sail2D repository.
Thanks for reading!
Thanks for reading!