Johnston, LJ 2009, Computation of multi-element aerofoil, high-lift aerodynamics at transonic flow conditions using transport equation turbulence models , in: 3rd European Conference for AeroSpace Sciences, July 6-9, 2009, Versailles, France.
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An unstructured-grid, Navier-Stokes flow solver is used to compute the transonic flow development over the SKF 1.1 supercritical aerofoil section, in clean configuration and equipped with either a trailing-edge flap or a leading-edge slat. A full differential Reynolds-stress turbulence model is employed, with wall-function near-wall boundary conditions, for the computations. Agreement between predicted surface pressure distributions and experimental data for the three high-lift configurations is satisfactory for the free-stream Mach number of 0.6 considered, over a range of incidence angles. There are some uncertainties in the wind-tunnel wall interference corrections to be applied to the experimental data, and there are also indications of possible leading-edge slat movement in the experiment under the large aerodynamic loads experienced in the cases considered.
|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 > School of Computing, Science and Engineering > Salford Innovation Research Centre (SIRC)|
|Depositing User:||LJ Johnston|
|Date Deposited:||10 Dec 2009 11:26|
|Last Modified:||30 Nov 2015 23:58|
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