Design of a model propulsor for a boundary layer ingesting aircraft
Author(s)
Grasch, Adam D. (Adam Davis)![Thumbnail](/bitstream/handle/1721.1/85778/871341962-MIT.pdf.jpg?sequence=5&isAllowed=y)
DownloadFull printable version (14.26Mb)
Other Contributors
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.
Advisor
Edward M. Greitzer.
Terms of use
Metadata
Show full item recordAbstract
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.
Description
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013. Cataloged from PDF version of thesis. Includes bibliographical references (pages 113-115).
Date issued
2013Department
Massachusetts Institute of Technology. Department of Aeronautics and AstronauticsPublisher
Massachusetts Institute of Technology
Keywords
Aeronautics and Astronautics.