Interference Drag Modeling and Experiments for a High-Reynolds-Number Transonic Wing.

This study assessed turbulence models for high-Reynolds-number transonic junction flows by comparing flow separation characteristics obtained from experiment and computational fluid dynamics. The test model used was a NACA 0012 wing of aspect ratio 2 at a Mach number of 0.76 and a Reynolds number of 6 ⋅ 106 with varying angles of attack. The computational fluid dynamics study involved an 18.8-million-cell structured grid of the wind-tunnel test section using the ANSYS Fluent 12.0 solver. The k-ω shear stress transport turbulence model was the main turbulence model employed. Experiments were conducted in a high-Reynolds-number transonic Ludwieg tunnel. The wing was simulated at different Mach numbers and inlet conditions to account for some of the experimental uncertainties. Porous walls eliminated shock reflection across the tunnel. Surface oil-flow visualization was used to indicate the interference flow patterns. The assessment shows that computational fluid dynamics overpredicts separation and therefore interference drag, likely due to deficiencies in the turbulence model. [ABSTRACT FROM AUTHOR]