A numerical investigation of a fully three-dimensional swept wing geometry featuring separation from a curved leading edge is presented. The Implicit Large-Eddy Simulation strategy based on a third-order high-resolution method for discretising the advective fluxes and a third-order Runge-Kutta time-stepping scheme with extended stability region has been employed. No attempt to incorporate a wall-model has been made. Instead, the boundary layer is fully resolved over the majority of the wing. Qualitative and quantitative comparisons with experimental oil-film visualisations and three-dimensional LDA measurements show very good agreement between the experiment and the numerically predicted flow structures, as well as velocity and stress profiles near the wing. Furthermore, data from a hybrid RANS/LES simulation has been included for comparison.
|Publication status||Published - 10 Jan 2008|
|Event||46th AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States|
Duration: 7 Jan 2008 → 10 Jan 2008
|Conference||46th AIAA Aerospace Sciences Meeting and Exhibit|
|Period||7/01/08 → 10/01/08|
- advective flux
- high-resolution methods
- hybrid RANS/LES
- LDA measurements
- numerical investigations
- aerospace engineering
- large eddy simulation
- Runge Kutta methods
- wing geometry
Hahn, M., & Drikakis, D. (2008). Implicit Large-Eddy Simulation for swept wing flow using high-resolution methods. Paper presented at 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.