Abstract
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.
| Original language | English |
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| 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
| Conference | 46th AIAA Aerospace Sciences Meeting and Exhibit |
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| Country/Territory | United States |
| City | Reno, NV |
| Period | 7/01/08 → 10/01/08 |
Keywords
- advective flux
- high-resolution methods
- hybrid RANS/LES
- LDA measurements
- numerical investigations
- aerospace engineering
- large eddy simulation
- Runge Kutta methods
- wing geometry