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Comparison of predictions with measurements for a quiet supersonic tunnelNavier-Stokes and boundary layer calculations were made to study the mean flow through the Montana State University Mach 3 supersonic wind tunnel. Two-dimensional results along the nozzle surface are found to be in good agreement with experiment. For the sidewalls a 3D solution was necessary because of a skew-induced secondary flow that produced significant crossflows in the sidewall boundary layer and thickening of the boundary layer near the sidewall centerline. Boundary layer stability calculations revealed Goertler instabilities in the nozzle producing N factors up to 6. Preliminary results for the crossflow instability on the tunnel sidewall show a maximum N factor of about 2.5 under test conditions for which laminar flow was observed experimentally.
Document ID
19930039034
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
King, Lyndell S.
(NASA Ames Research Center Moffett Field, CA, United States)
Demetriades, Anthony
(Montana State Univ. Bozeman, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 93-0344
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A23031
Distribution Limits
Public
Copyright
Other

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