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Enhanced Performance of Streamline-Traced External-Compression Supersonic InletsA computational design study was conducted to enhance the aerodynamic performance of streamline-traced, external-compression inlets for Mach 1.6. The current study explored a new parent flowfield for the streamline tracing and several variations of inlet design factors, including the axial displacement and angle of the subsonic cowl lip, the vertical placement of the engine axis, and the use of porous bleed in the subsonic diffuser. The performance was enhanced over that of an earlier streamline-traced inlet such as to increase the total pressure recovery and reduce total pressure distortion
Document ID
20160000595
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
Slater, John W. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
January 11, 2016
Publication Date
October 25, 2015
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
GRC-E-DAA-TN27519
Report Number: GRC-E-DAA-TN27519
Meeting Information
Meeting: International Symposium on Airbreathing Engines (ISABE)
Location: Phoenix, AZ
Country: United States
Start Date: October 25, 2015
End Date: October 30, 2015
Sponsors: International Society for Air Breathing Engines (ISABE)
Funding Number(s)
WBS: WBS 110076.02.03.03.04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
performance
inlets
supersonic

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