Design of a model propulsor for a boundary layer ingesting aircraft

[摘要] This thesis presents contributions to the analysis and design of propulsion simulators for 1:11 and 1:4 scale model wind tunnel investigations of an advanced civil transport aircraft with boundary layer ingestion (BLI). The electrically powered single-stage propulsors represent the ultra-high bypass ratio turbofan engines on a full-scale conceptual aircraft previously designed at MIT. Powered models will use these propulsors in both podded and boundary layer ingesting configurations to allow back-to-back assessment of BLI benefit. The thesis gives a description of work on propulsion system scaling, nacelle and flowpath aerodynamic optimization, mechanical design of the propulsor and characterization of the propulsor electric motors, all in support of the wind tunnel experiments. Explicit definition is given of those designs that meet the requirements of the program as well as those in which there are items still to be addressed.

[发布机构] Massachusetts Institute of Technology