Unstructured grid generation method and flow solutions for two-dimensional, high-lift aerofoil configurations
Marques, SP and Johnston, LJ 2007, Unstructured grid generation method and flow solutions for two-dimensional, high-lift aerofoil configurations , in: 45th AIAA Aerospace Sciences Meeting and Exhibit, 8-11 January, 2007, Reno, Nevada, USA.
Restricted to Repository staff only
Download (7MB) | Request a copy
An unstructured grid generation method, developed for particular application to multi-element, high-lift aerofoil configurations operating at high-Reynolds number conditions, is presented. The grid generation method starts by creating anisotropic triangular computational cells around the aerofoil elements, in order to provide adequate resolution of boundary layer and wake regions. The remainder of the flow domain is then triangulated, using an edge-splitting algorithm that creates new computational cells, grid points and cell connectivities simultaneously. Flow solutions are obtained by solving the Reynolds-averaged Navier-Stokes equations, in conjunction with a differential Reynolds stress turbulence model and wall function boundary conditions. Results for 3-, 4- and 5-element aerofoil configurations are presented and compared with experimental measurements obtained during the UK’s National High Lift Programme of the 1970s.
|Item Type:||Conference or Workshop Item (Paper)|
|Themes:||Subjects / Themes > T Technology > TL Motor vehicles. Aeronautics. Astronautics
Subjects outside of the University Themes
|Schools:||Schools > College of Science & Technology
Schools > College of Science & Technology > School of Computing, Science and Engineering > Salford Innovation Research Centre (SIRC)
|Depositing User:||LJ Johnston|
|Date Deposited:||10 Dec 2009 11:48|
|Last Modified:||29 Oct 2015 00:19|
Actions (login required)
|Edit record (repository staff only)|