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Vortex Generators in a Two-Dimensional, External-Compression Supersonic InletComputational fluid dynamics simulations are performed as part of a process to design a vortex generator array for a two-dimensional inlet for Mach 1.6. The objective is to improve total pressure recovery a on at the engine face of the inlet. Both vane-type and ramp-type vortex generators are examined.
Document ID
20170002631
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
Baydar, Ezgihan (Texas Univ. Arlington, TX, United States)
Lu, Frank K. (Texas Univ. Arlington, TX, United States)
Slater, John W. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
March 29, 2017
Publication Date
July 25, 2016
Subject Category
Aeronautics (General)
Fluid Mechanics And Thermodynamics
Report/Patent Number
GRC-E-DAA-TN33924
Report Number: GRC-E-DAA-TN33924
Meeting Information
Meeting: AIAA/SAE/ASEE Joint Propulsion Conference 2016
Location: Salt Lake City, UT
Country: United States
Start Date: July 25, 2016
End Date: July 27, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 110076.02.03.04.10
CONTRACT_GRANT: NNX13AR81H
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
supersonic inlets
computational fluid dynamics
vortex generators

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