A moveable block planar nozzle wind tunnel design from the University of Michigan in 1955 was shown with previous analysis to operate between Mach 1 and at least Mach 6.3 for mid-size test sections, with continuous variation in Mach number and accounting for limitations governed by supply temperature and pressure, liquefaction, flow rate, and flow quality for a desired dynamic pressure or Reynolds number. The moveable block planar nozzle design allows for continuous variation of Mach number, based on a Method of Characteristics solution to a convergent-divergent nozzle with a boundary layer correction. The present work summarizes the design considerations and hardware performance requirements for such a tunnel in the blowdown configuration, with a comparison between cold and hot operation for various test section sizes and supply conditions. The flow quality is compared between a two planar nozzles and an axisymmetric nozzle for a 12×12[in] test section, the effect of physical scaling on flow quality and boundary layer encroachment is investigated across scales of 1×1” to 12×12” test sections at Mach 5, and the merits of planar nozzle aspect ratios greater than unity are presented and discussed.
- Fluids Engineering Division
Design and Performance of a Hypersonic Wind Tunnel
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Maxwell, J. "Design and Performance of a Hypersonic Wind Tunnel." Proceedings of the ASME 2017 Fluids Engineering Division Summer Meeting. Volume 1B, Symposia: Fluid Measurement and Instrumentation; Fluid Dynamics of Wind Energy; Renewable and Sustainable Energy Conversion; Energy and Process Engineering; Microfluidics and Nanofluidics; Development and Applications in Computational Fluid Dynamics; DNS/LES and Hybrid RANS/LES Methods. Waikoloa, Hawaii, USA. July 30–August 3, 2017. V01BT06A016. ASME. https://doi.org/10.1115/FEDSM2017-69439
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