Topics on conceptual design of the D8 aircraft : fuel burn uncertainty estimate and BLI propulsor loss modeling
Name
1008568359-MIT.pdf
Description
Full printable version
Size
12.91 MB
Format
Adobe PDF
Checksum (MD5)
2215dff822903ebb9a6028edb3847969
Author(s)
Chen, Yuankang (Aerospace engineer) Massachusetts Institute of Technology
Advisor(s)
Alejandra Uranga, David K. Hall and Edward M. Greitzer.
Date Issued
2017
Publisher
Massachusetts Institute of Technology
Abstract
This thesis addresses two topics related to the D8 transport aircraft, developed by MIT under NASA's N+3 program. The first is the reduction in fuel burn specifically attributable to the novel design features of the D8, which include a lifting nose, a double bubble fuselage, and aft mounted engines that ingest part of the fuselage boundary layer. This fuel burn benefit is determined to be (18.0 ± 2.2)% for aircraft with a cruise Mach of 0.72 and (20.1 ± 2.6)% for aircraft with a cruise Mach of 0.78. The benefit is shown to be robust to changes in technology assumptions and uncertainty in specified design parameters. The presented results refine previous conceptual studies and provide strong support for further development of the D8 by reducing the uncertainty in its performance estimates. The second topic addressed in this thesis is the modeling of Boundary Layer Ingesting (BLI) propulsor losses at a level of fidelity appropriate for turbomachinery conceptual design analysis, i.e. nonaxisymmetric throughflow analysis. Two contributions to such an analysis based on a body force framework are presented in this thesis: a description of blade profile losses in incompressible flow, and a roadmap for the development of corrections that capture the endwall effects on the flow through the propulsor.
Description
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 131-133).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
MIT theses are protected by copyright. They may be viewed, downloaded, or printed from this source but further reproduction or distribution in any format is prohibited without written permission.
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