Abstract
Numerical simulation method for the prediction of supersonic intake performance is discussed. To perform a practical simulation, it is necessary to consider not only the nacelle-only configuration but also the engine/airframe configuration. In this study, the unstructured mesh, known to have advantages with regard to adaptation to complex geometry, was generated around aircraft geometry and the Euler equation was solved. To obtain higher numerical accuracy for the shock wave/boundary layer interaction, which appears at the inlet, the structured Navier-Stokes solver was applied to solve flows inside the flow-through nacelle. These regions were coupled with using the unstructured-structured zonal approach. The nacelle-only configuration and the engine/airframe configuration were calculated using this method and the effects of the airframe existence on supersonic intake performance were investigated.
