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- W2316916306 abstract "The Arnold Engineering Development Center (AEDC) Hypervelocity Wind Tunnel No. 9 facility has played a key role in the development of hypersonic vehicles for over 30 years, providing high-quality aerodynamic and aerothermal test data covering high Mach number and high Reynolds number flight simulations. Although Tunnel 9 can achieve flight level Reynolds numbers and naturally transitioning boundary layers on most test articles, the presence of “tunnel noise” can complicate the understanding of the boundary-layer transition phenomenon. In an attempt to better characterize the freestream disturbances described as “tunnel noise” a set of data was collected using a flush-mounted Pitot acoustic probe. The data quantify the relative Pitot acoustic noise of the freestream flow for the Mach 8, 10, and 14 nozzles at AEDC Tunnel 9. The percent noise level for each nozzle varied on the basis of Reynolds number from approximately 2 to 3.5 percent at Mach 8, 2.5 to 4 percent at Mach 10, and 3.75 to 6.25 percent at Mach 14." @default.
- W2316916306 created "2016-06-24" @default.
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- W2316916306 date "2007-02-13" @default.
- W2316916306 modified "2023-10-16" @default.
- W2316916306 title "Measurements of Fluctuating Pitot Pressure, Tunnel Noise, in the AEDC Hypervelocity Wind Tunnel No. 9" @default.
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- W2316916306 doi "https://doi.org/10.2514/6.2007-1678" @default.
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