Boundary layer ingesting inlet design for a silent aircraft

(cont.) common nacelle, L/D ratios between 2.5 and 3.0, fan face to throat area ratios above 1.06, and offsets lower than 11%. Curvature ahead of the inlet should be avoided as well as bifurcations inside the duct. Inlet performance with an evolved version of the airframe decreased, mainly due to a thicker boundary layer. Although further tailoring of the geometry is needed, the above guidelines should provide both direction and rationale for these alterations.

Department dc:contributor.department

Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2005

Author dc:creator

• Freuler, Patrick N., 1980-

Advisor dc:contributor.advisor

• Wesley Harris, Edward M. Greitzer and Mark Drela.

• 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

en_US

Handle dc:identifier.uri

http://hdl.handle.net/1721.1/28903

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/28903