Abstract
Supersonic flow of nitrogen gas through miniature nozzles of planar configuration was investigated experimentally and compared with numerical simulations to assess the applicability and accuracy of the various viscous-flow models. The design Mach number of the nozzles is 3, and the inlet pressures range from 0 to 10 atm (gauge). The measured thrust of the meso nozzle with a throat area of 0.773 mm2 agreed well with the numerical solution (96%). The agreement of the micro nozzle, with a throat area of 0.0625 mm2, decreased to 80% for pressure differences beyond the design flow condition. At low-pressure differences, separated flow occurred after the shock in the nozzle, causing unstable and asymmetric velocity distributions on the nozzle exit plane. Thrust was found to be not only a function of pressure difference but also a function of the flow history. The numerical simulation was successful in modeling these effects, but at different pressures.
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