Towards High-Fidelity Computation of an Installed Open Fan-Nozzle Configuration

Consider a next-generation open fan and exhaust nozzle mounted on an aircraft wing. In this installed configuration, there are interaction effects between the engine and the wing that can affect the overall aerodynamic and aero-acoustic performance of the system. The wake and vorticity generated by the open fan convect downstream and can interact with the flow over the wing. The jet from the exhaust nozzle can interact with the deployed high lift devices. Conversely the flow field induced by the wing can affect the performance of the fan and the exhaust nozzle. Such effects are naturally not captured in isolated simulations of the open fan (e.g., Priebe et al [1], Karve et al. [2]), nor are they captured in isolated simulations of the wing (e.g., Wang and Hantla [3]). High-fidelity simulations of the combined engine and aircraft configuration are required. Wall-Resolved LES (WRLES) is computationally expensive particularly at the high Reynolds numbers encountered at full-scale flight conditions. A validated and robust Wall-Modeled LES (WMLES) capability is thus necessary. The current paper discusses the progress of validating WMLES for various flow regimes one would encounter on a fully installed configuration.