Computation of multi-element aerofoil, high-lift aerodynamics at transonic flow conditions using transport equation turbulence models

Johnston, LJ

Abstract

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.

Citation

Johnston, L. (2009, July). Computation of multi-element aerofoil, high-lift aerodynamics at transonic flow conditions using transport equation turbulence models. Presented at 3rd European Conference for AeroSpace Sciences, Versailles, France

• Presentation Conference Type: Other
• Conference Name: 3rd European Conference for AeroSpace Sciences
• Conference Location: Versailles, France
• Start Date: Jul 6, 2009
• End Date: Jul 9, 2009
• Publication Date: Jan 1, 2009
• Deposit Date: Dec 10, 2009
• Publicly Available Date: Dec 10, 2009
• Additional Information: Corporate Creators : School of Computing, Science & Engineering; Event Type : Conference