Title page for ETD etd-07112008-182200


Type of Document Master's Thesis
Author Hylton, Michael Ronnie
URN etd-07112008-182200
Title Assessment of an Innovative Experimental Facility for Testing Diffusing Serpentine Inlets with Large Amounts of Boundary Layer Ingestion
Degree Master of Science
Department Mechanical Engineering
Advisory Committee
Advisor Name Title
Ng, Fai Committee Co-Chair
O'Brien, Walter F. Jr. Committee Co-Chair
Dancey, Clinton L. Committee Member
Keywords
  • Boundary-Layer-Ingesting
  • Blended-Wing-Body
  • Aerodynamic Interface Plane
  • Serpentine Inlet
  • Distortion
Date of Defense 2008-07-09
Availability unrestricted
Abstract
An innovative experimental facility was developed for testing flush-mounted, diffusing serpentine inlets intended for use on blended-wing-body aircraft. The static ground test facility was able to simulate the boundary layer profile expected to be ingested by inlets mounted on the aft sections of these aircraft. It generated Mach numbers ranging from 0.19 to 0.4 and boundary layer thicknesses between 36% and 45%. The circumferential distortions at the aerodynamic interface plane of the serpentine inlet were also calculated, and ranged between 0.0042 for the lowest Mach number, to 0.0098 for the highest Mach number. Reynolds numbers for the tests ranged between 1.2 million and 2.4 million depending on engine speed and Mach number. The results of the experiment were compared to a previous NASA report, and showed close agreement in distortion patterns and pressure losses at a Mach number of 0.25.
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