The complex flow physics generated by high lift systems poses significant challenges to CFD codes. This list of flow physics includes laminar flow, attachment line transition, relaminarization, transonic slat flow, confluent boundary layers, wake interactions, separation, and reattachment. Even in two-dimensional flows, state-of-the-art codes are unable to consistently predict increments in performance due to changes in Reynolds number and slat/flap positioning.
Recently, advances in grid generation techniques, solvers, and increases
in computing power have enabled the analysis of high lift systems in 3D.
Validation of this emerging capability against representative high lift
flow fields is needed if these tools are to be adopted by industry with
confidence.
The overall test objective was to obtain detailed wind tunnel datasets
that allow assessment / validation of Navier-Stokes methods over a range
of Reynolds number. The experiment was designed to establish a ‘representative’
high lift flow on a geometrically simplified configuration. By ‘representative’,
we mean a flow field that can reproduce – through combinations of slat
and flap deflection, gap, overlap, angle-of-attack, Mach, and Reynolds
number – the flow physics characteristic of subsonic transport high lift
flows. On a geometrically simplified configuration, grid generation is
simplified, and the computing requirements for grid-independent, converged
solutions are considerably reduced.
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Page Curator and NASA Official Responsible for Content
Judith A. Hannon
Last Updated
August 5, 2011