Search

• The experimental results show that the wall significantly changes the mean pressure distribution around the wing. • The comparisons of the experimental and numerical results indicates that the γ - R e θ SST model is a good choice for junction flow simulations at the preliminary design stage. • The Reynolds Stress models, however, do not show any advantage in predicting the mean pressure field. A junction flow formed between a wing and a wall is ubiquitous in engineering applications and impacts aerodynamic performance and energy consumption. This paper studies the mean pressure field in the junction region around wall-mounted wings with NACA 0012 and NACA 6412 wing section profiles. Mean surface pressure measurements have been performed in the University of New South Wales large aerodynamic wind tunnel at a chord-based Reynolds number of 87,000 and a range of angles of attack spanning 0 - 12 degrees. Results of three-dimensional RANS simulations for both wing profiles using five turbulence models are also presented. The experimental results show that the wall significantly changes the mean pressure distribution around the wing, especially in the region upstream of the boundary layer reattachment point. The γ - R e θ SST turbulence model has a transition predictor for the boundary layer above the airfoil far away from the bottom wall and delivers the most accurate pressure field prediction in the wing-wall junction region. The junction pressure structure is well-captured except the LE stagnation region and the suction side of the trailing edge. The Reynolds Stress models, however, do not show any advantage in predicting the mean pressure field at high angles of attack. [ABSTRACT FROM AUTHOR]