Compressible Navier-Stokes Calculations of the Flow Over Airfoil Sections. Comparison of 1st and 2nd Order Turbulence Models 932510
We present preliminary results from a study of the ability of various turbulence models to predict airfoil stall angle, as compared with one of the few modern data sets, from tests of the Aerospatiale airfoil AS240 in the ONERA wind tunnel of Fauga, France [1,2]. We first compared the Chien k - ε model , the Wilcox k - ω model , and the most recent version of the Launder-Reece-Rodi Reynolds-Stress Transport Model (RSTM) , in a boundary layer in zero pressure gradient. The k - ω model and the RSTM models were chosen for the airfoil calculations.
Citation: Masson, B., Huang, G., and Bradshaw, P., "Compressible Navier-Stokes Calculations of the Flow Over Airfoil Sections. Comparison of 1st and 2nd Order Turbulence Models," SAE Technical Paper 932510, 1993, https://doi.org/10.4271/932510. Download Citation
Bertrand Masson, George Huang, Peter Bradshaw
Aerospace Technology Conference and Exposition