High-Order Simulation of Aeronautical Separated Flows with a Reynold Stress Model

Based on the symmetrical conservative metric method, the high-order weighted compact nonlinear schemes with the Speziale–Sarkar–Gatski/Launder–Reece–Rodi- Reynolds stress model are applied to a series of separated flow cases in aeronautics. The relevant cases include the NASA CW-22 transonic turbine cascade, the NASA Common Research Model wing–body configuration, and the wingtip vortex on a NACA 0012 half-span wing. To assess the Reynolds stress model’s predictive capabilities, simulation results are compared with predictions by weighted compact nonlinear schemes with the Menter shear-stress transport model. Moreover, to demonstrate the advantage of high-order methods for separated flow simulations, the second-order method MUSCL is also adopted for comparisons.