Johnston, LJ 2009, Aerodynamic analysis of transonic manoeuvre devices using an unstructured-grid, Navier-Stokes flow solver , in: CEAS 2009 European Air and Space Conference, 26-29 October, 2009, Manchester, United Kingdom.
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The viscous, transonic flow development around the SKF 1.1 supercritical aerofoil section, in clean configuration and equipped with either a trailing-edge flap or a leading-edge slat, is computed using an unstructured-grid based flow solver for the Reynolds-averaged Navier-Stokes equations. A full differential Reynolds-stress turbulence model is employed in the computations to model the Reynolds stresses appearing in the mean-flow equations. The wall-function approach is adopted to bridge the molecular-viscosity dominated region immediately adjacent to solid boundaries. Predicted surface pressure distributions are compared with experimental data, for a free-stream Mach number of 0.6 and a range of incidence angles, and generally show a satisfactory level of agreement. There are some discrepancies in the region of the upper surface shock wave/boundary layer interactions that are probably partially due to uncertainties in the wind-tunnel wall interference corrections to be applied to the experimental data. However, the influence of the near-wall treatment in the computations also requires further investigation.
|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 11:36|
|Last Modified:||30 Nov 2015 23:58|
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