Effect of a Splitter Plate on Transonic Wing Flow: A Numerical Study

摘要

IN the experimental analysis of the flow around isolated wings, semimodels mounted on a sidewall are widely used. Indeed, this approach is very attractive, because supports are not needed, and, hence, the effects of the interference between models and supports are eliminated. On the other hand, the flow at the root of the semi- model is clearly different from that at the symmetry plane of the isolated wing, due to the effect of the sidewall boundary layer, as pointed out in Ref. 1 for a low-aspect-ratio wing. To reduce this effect, the model is commonly offset from the tunnel sidewall by means of a splitter plate. Nevertheless, even in this case, the splitter- plate boundary layer may significantly affect the experimental data.