Evaluation of propulsor aerodynamic performance for powered aircraft wind tunnel experiments

This thesis describes a methodology to convert electrical power measurements to propulsor mechanical ow power for a 1:11-scale, powered wind tunnel model of an advanced civil aircraft utilizing boundary layer ingestion (BLI); mechanical ow power is a surrogate for aircraft fuel burn. Back-to-back experiments of BLI and non-BLI aircraft configurations to assess the BLI benet directly measured electrical power, and supporting experiments were performed in a 1x1 foot wind tunnel at the MIT Gas Turbine Laboratory to convert these measurements into mechanical flow power. The incoming flow conditions of the powered wind tunnel tests (Reynolds number and inlet distortion) were replicated. This propulsor characterization was found to convert the electrical power measurements to mechanical ow power with experimental uncertainty of roughly 1.6%.

Department dc:contributor.department

Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2015

Author dc:creator

• Siu, Nina M

Advisor dc:contributor.advisor

• Edward M. Greitzer and Alejandra Uranga.

• 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/1721.1/97265

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/97265