Design of a model propulsor for a boundary layer ingesting aircraft
Name
871341962-MIT.pdf
Description
Full printable version
Size
14.26 MB
Format
Adobe PDF
Checksum (MD5)
152599bda8e1fc8643ef991f297ec73b
Author(s)
Grasch, Adam D. (Adam Davis)
Advisor(s)
Edward M. Greitzer.
Date Issued
2013
Publisher
Massachusetts Institute of Technology
Abstract
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).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
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