Pressure Fluctuations in a Hypersonic Ludwieg Tube with Free Piston Compression Heating
Paper
Paper/Presentation Title | Pressure Fluctuations in a Hypersonic Ludwieg Tube with Free Piston Compression Heating |
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Presentation Type | Paper |
Authors | Birch, Byrenn J. C. (Author), Choudhury, Rishabh (Author), Stern, Nathan (Author) and Buttsworth, David R. (Author) |
Journal or Proceedings Title | Proceedings of the 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference |
ERA Conference ID | 60012 |
Number of Pages | 23 |
Year | 2018 |
Place of Publication | Reston, United States |
ISBN | 9781510875425 |
9781624105777 | |
Digital Object Identifier (DOI) | https://doi.org/10.2514/6.2018-5266 |
Web Address (URL) of Paper | https://arc.aiaa.org/doi/10.2514/6.2018-5266 |
Conference/Event | 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference (AIAA 2018) |
AIAA International Space Planes and Hypersonic Systems and Technologies Conference | |
Event Details | 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference (AIAA 2018) Event Date 17 to end of 19 Sep 2018 Event Location Orlando, United States |
Event Details | AIAA International Space Planes and Hypersonic Systems and Technologies Conference |
Abstract | The free stream acoustic disturbance environment in hypersonic wind tunnel testing has a significant impact on boundary layer stability and transition to turbulence, and can influence the results of fluid-structure interaction studies. The pressure disturbance level and spectral content of the University of Southern Queensland’s Mach 6 Ludwieg tube with free piston compression facility is identified via pitot pressure measurements that were analyzed using a high-pass filter method and a power spectral density technique. Using the power spectral density method, the acoustic environment was found to change properties during the run, and it was therefore appropriate to define two root-mean-square percentage pressure fluctuation levels across frequencies from 300 Hz to 25 kHz: 2.53 % in the run period from 5 to 85 ms, and 2.98 % from 85 to 200 ms. The sensitivity of the root-mean-square results of the power spectral density analysis to the windowing technique was minimized through the assessment and selection of appropriate windowing parameters. Results obtained using this optimized windowing method compare favorably with the more traditional high pass filter analysis method. |
Keywords | Acoustic disturbances; Acoustic environment; Boundary layer stabilities; Hypersonic wind tunnels; Power spectral density analysis; Power spectral density method; Pressure fluctuation; Transition to turbulence |
ANZSRC Field of Research 2020 | 400106. Hypersonic propulsion and hypersonic aerothermodynamics |
Public Notes | Files associated with this item cannot be displayed due to copyright restrictions. |
Byline Affiliations | School of Mechanical and Electrical Engineering |
Institution of Origin | University of Southern Queensland |
https://research.usq.edu.au/item/q6598/pressure-fluctuations-in-a-hypersonic-ludwieg-tube-with-free-piston-compression-heating
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