FLOW CHARACTERIZATION OF THE NAVAL POSTGRADUATE SCHOOL'S MACH 4 WIND TUNNEL
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Authors
Plum, Max J.
Subjects
wind tunnel
Mach 4
rake probe
Kulite
acoustic noise
acoustic intensity
Mach 4
rake probe
Kulite
acoustic noise
acoustic intensity
Advisors
Hobson, Garth V.
Smith, Walter C.
Date of Issue
2024-06
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
With the Naval Postgraduate School recently taking up an effort to study supersonic and hypersonic inlet un-start, the school’s Mach 4 Supersonic Wind Tunnel (SSWT) was renovated to achieve a quieter and more uniform flow field. An effort was made to characterize the tunnel’s Mach number, acoustic intensity, and turbulence intensity profiles across the test section using both computational modeling and experimental testing. Computational modeling utilized ANSYS CFX to generate a baseline Mach profile for comparison with experimental data. The model predicted a reasonably uniform flow field with a pair of counter-rotating vortices stemming from the nozzle exit that traveled into the test section along the sidewall. Experimental testing consisted of stationary and traversing Kulites and total pressure probes to characterize the acoustic intensity and Mach number across both the freestream and boundary layers. Total pressure probe testing confirmed the presence of large vortices in the boundary layer, but also discovered large asymmetries across the width of the tunnel. Kulite acoustic intensity values were calculated at 2.4 to 2.5%, and a normal shock vibrational frequency was found around 60 kHz. All testing proved to be incredibly repeatable between tunnel runs, but not probe to probe. Testing also included the attempted use of a hot film probe to characterize turbulence intensity; however, the results were inconclusive and yielded no useful information on the tunnel.
Type
Thesis
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Distribution Statement
Distribution Statement A. Approved for public release: Distribution is unlimited.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.