Designing and Testing a Blended Wing Body with Boundary-Layer Ingestion Nacelles

摘要

A knowledge-based aerodynamic design method coupled with an unstructured grid Navier-Stokes flow solver was used to improve the propulsion/airframe integration for a blended wing body with boundary-layer ingestion nacelles. A new zonal design capability was used that significantly reduced the time required to achieve a successful design for each nacelle and the elevon between them. A wind-tunnel model was built with interchangeable parts reflecting the baseline and redesigned configurations and tested in the National Transonic Facility. Most of the testing was done at the cruise design conditions (Mach number of 0.85, Reynolds number of 75 million). In general, the predicted improvements in forces and moments as well as the changes in wing pressures between the baseline and redesign were confirmed by the wind-tunnel results. The effectiveness of elevons between the nacelles was also predicted surprisingly well considering the crudeness in the modeling of the control surfaces in the flow code.