Abstract
For a three-dimensional half-model high-lift configuration in a wind-tunnel environment, flow separation near maximum lift is influenced by the presence of geometric details. To examine the influence of these details, three computationalfluid dynamics based studies are carried out. The objective is to examine the influence of pressure tube bundles, wind-tunnel walls andmodelmounting, and the effect ofmodel deformation for a high-lift wind-tunnel halfmodel. Viscous flow computations for a high-lift configuration including pressure tubes and wind-tunnel walls (and model mounting) are performed. Experiences gathered with these flow computations are reported and comparisons to wind-tunnel experiments are made. Four methods are deployed in order to study aeroelastic effects, namely, a lifting surface based aeroelastic method and three fully coupledmethods. Three structural models of a high-lift wing are developed. Experiences with three fully coupled methods are reported and benefits and shortcomings are identified. It is concluded that geometrical installation and deformation effects for a half-model high-lift wing in a wind-tunnel environment are significant. The mounting of the half-model has the most significant effect on the aerodynamic coefficients.
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