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The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets

Abstract The objective of this study is to understand how to integrate conical spike external compression inlets with high bypass turbofan engines for application on future supersonic airliners. Many performance problems arise when inlets are matched with engines as inlets come with a plethora of limitations and losses that greatly affect an engine’s ability to operate. These limitations and losses include drag due to inlet spillage, bleed ducts, and bypass doors, as well as the maximum and minimum values of mass flow ratio at each Mach number that define when an engine can no longer function. A collection of tools was developed that allow one to calculate the raw propulsion data of an engine, match the propulsion data with an inlet, calculate the a... (more)
Created Date 2018
Contributor Cleary, Spencer (Author) / Takahashi, Timothy (Advisor) / White, Daniel (Committee member) / Dahm, Werner (Committee member) / Arizona State University (Publisher)
Subject Aerospace engineering / External Compression Inlets / High Bypass Turbofan Engines / Supersonic Aircraft Performance / Supersonic Airliners / Supersonic Propulsion Performance
Type Masters Thesis
Extent 123 pages
Language English
Reuse Permissions All Rights Reserved
Note Masters Thesis Aerospace Engineering 2018
Collaborating Institutions Graduate College / ASU Library
Additional Formats MODS / OAI Dublin Core / RIS

  Full Text
3.1 MB application/pdf
Download Count: 1174

Description Dissertation/Thesis
  NPSS Input and Output
1.8 MB application/zip
Download Count: 3

Description Run file and text files from the propulsion simulations performed in NPSS.
  EDET Input and Output
7.9 KB application/zip
Download Count: 1

Description Input and output file used in EDET to generate aerodynamic data of Concorde.
  Five Column Propulsion
894.0 KB application/zip
Download Count: 1

Description Five column propulsion data of tested engines after inlet matching.