Design of a model propulsor for a boundary layer ingesting aircraft

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.

Department dc:contributor.department

Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2013

Author dc:creator

• Grasch, Adam D. (Adam Davis)

Advisor dc:contributor.advisor

• Edward M. Greitzer.

• Aeronautics and Astronautics.

Statement dc:rights

• M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.

Licence dc:rights.uri

• http://dspace.mit.edu/handle/1721.1/7582

Language dc:language.iso

eng

Handle dc:identifier.uri

http://hdl.handle.net/1721.1/85778

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/85778