Wall Modeled LES of the NASA Juncture Flow Model with Transition Sensor Treatment

Wall-Modeled Large Eddy Simulations (WMLES) face inherent limitations in accurately capturing leading-edge laminar boundary layers and trailing-edge separation over aerodynamic surfaces. In this study, we perform WMLES of the NASA Juncture Flow Model (JFM) symmetric wing configuration at a 5 degree angle of attack, Reynolds number 2.4 million (based on crank chord) and Mach number 0.189 to assess capability of equilibrium wall model in predicting key mean flow features and corner-flow separation in a wing‑body juncture. The primary objective is to evaluate the performance of WMLES in reproducing experimental observations of the mean flow. As a secondary objective, we apply a transition-sensor-based treatment near the leading edge to address the inability of conventional WMLES to resolve laminar-to-turbulent transition.