The Numerical Simulation of Civil Transportation High-lift Configuration

The complex multiform flow phenomenon including boundary layer transition, lamination separation, turbulence attach line and re-lamination, boundary shock interaction and so on will appear when the air flow over the high lift configuration, which makes it very difficult to predict by numerical simulation. In order to validate the CFD code prediction capability of high lift configuration of swept wing with high aspect ratio, AIAA held two workshops of CFD high lift prediction in 2010 and 2012. The NASA Trapwing model and DLR-F11 model were chosen to research the mesh resolution, turbulence model, transition prediction and Reynolds effect by numerical simulation. Based on the published work of the1st and 2nd high lift prediction workshop, some numerical simulation research to validate the rationality of mesh generation are done in this paper. The two configurations of NASA Trapwing and DLR F-11 are simulated by solving the Reynolds-averaged Navior-Stokes equations with the S-A turbulence model. The numerical data in linear region agree very well with the experiments but the discrepancy between numerical data and experiment data near the stall region is perceptible. It can be conclude generally from the numerical results of two configurations that in the engineer design phase the Reynolds-averaged Navior-Stokes equations can give correct results of the aerodynamic characteristic with carefully generated mesh and appropriate turbulence model.