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Mach 5 inlet CFD and experimental resultsAn experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft supersonic wind tunnel. The 2-D inlet model was designed to study the Mach 3.0 to 5.0 speed range for an over-under turbojet plus ramjet propulsion system. The model was extensively instrumented to provide both analytical code validation data as well as inlet performance information. Support studies for the program include flow field predictions with both 3-D parabolized Navier-Stokes (PNS) and 3-D full Navier-Stokes (FNS) analytical codes. Analytical predictions and experimental results are compared.
Document ID
19890018299
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Weir, Lois J. (Sverdrup Technology, Inc., Cleveland OH., United States)
Reddy, D. R. (NASA Lewis Research Center Cleveland, OH, United States)
Rupp, George D. (Sverdrup Technology, Inc., Cleveland OH., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:102317
AIAA PAPER 89-2355
E-5011
NASA-TM-102317
Meeting Information
Meeting: Joint Propulsion Conference
Location: Monterey, CA
Country: United States
Start Date: July 10, 1989
End Date: July 12, 1989
Sponsors: ASEE, AIAA, ASME, SAE
Accession Number
89N27670
Funding Number(s)
PROJECT: RTOP 505-80-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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