Evaluation of propulsor aerodynamic performance for powered aircraft wind tunnel experiments
Name
910663649-MIT.pdf
Description
Full printable version
Size
1.68 MB
Format
Adobe PDF
Checksum (MD5)
d31b44f83b94b165996712793564aef7
Author(s)
Siu, Nina M
Advisor(s)
Edward M. Greitzer and Alejandra Uranga.
Date Issued
2015
Publisher
Massachusetts Institute of Technology
Abstract
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%.
Description
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Cataloged from student-submitted PDF version of thesis.
Includes bibliographical references (pages 91-92).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
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.
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