This study investigates laminar-to-turbulent transition behavior on the Pazy wing at a low chord Reynolds number (Rec = 1.2 \(\times\:{10}^{5}\) ) — a benchmark configuration from the AIAA Aeroelastic Prediction Workshops that was designed to study flexible wings experiencing large deformations. The wing geometry exhibits quasi-periodic spanwise variations in the cross-sectional shape, and we predict their influence on the overall aerodynamic characteristics via steady-state computations with two different transition models coupled with the Reynolds averaged Navier-Stokes (RANS) equations: the shear-stress-transport-based Langtry-Menter \(\varvec{\gamma\:}-\varvec{R}{\varvec{e}}_{\varvec{\theta\:}\varvec{t}}\) model and the Spalart-Allmaras-based amplification factor transport (AFT) model in NASA’s OVERFLOW solver. The results provide new insights into the strongly three-dimensional flowfield, as well as the transition characteristics of a flexible wing at pre-stall incidence angles. Our analysis reveals how small variation in section thickness between the rib (t/c = 17.6%) and sagged (t/c = 16.3%) portions of the wing can lead to significant differences in separation characteristics along the respective sections. Results also show that the overall 3D wing behavior more closely resembles the 2D characteristics of the sagged section rather than the nominal NACA 0018 airfoil (or the rib section). Both transition models indicate qualitative agreement with the available experimental data, accurately capturing trends in both 3D separation bubbles and the transition onset front under static, pre-stall loading conditions and low Rec. The results contribute valuable guidance for aerodynamic analyses of configurations relevant to small unmanned aerial vehicles, wind turbines, and other applications involving flexible lifting surfaces.
