Contributions of the unstructured Reynolds-averaged Navier-Stokes code, FUN3D, to the 3~(rd) AIAA Propulsion Aerodynamics Workshop are described for three diffusing IFCPT S-Duct configurations. Using workshop-supplied grids, results for the baseline S-Duct, S-Duct with Aerodynamic Interface Plane (AIP) rake assembly, and S-Duct with flow control devices are compared with experimental data and results computed with output-based, off-body grid adaptation in FUN3D. Due to the absence of influential geometry components, total pressure recovery is overpredicted on the baseline S-Duct and S-Duct with flow control vanes configurations when compared to experimental values. An estimate for the exact value of total pressure recovery is derived for these cases given an infinitely refined mesh. When results from output-based mesh adaptation are compared with those computed on workshop-supplied grids, a considerable improvement in predicting total pressure recovery is observed. By including more representative geometry, output-based mesh adaptation compares very favorably with experimental data in terms of predicting the total pressure recovery cost-function; whereas, results computed using the workshop-supplied grids are underpredicted.
展开▼
