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http://dx.doi.org/10.5139/JKSAS.2015.43.6.479

Study on Reflected Pressure in a Shock Tunnel According to the Size of a Nozzle Throat  

Lee, Jong Kook (Agency for Defense Development)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.43, no.6, 2015 , pp. 479-487 More about this Journal
Abstract
In a reflected shock tunnel, stagnation conditions of a nozzle are determined by the flow behind a reflected shock. When calculating the flow behind the reflected shock, unlike a shock tube, the flow leakage through the nozzle is to be considered. The analytical studies were done to find out the characteristics of the stagnation conditions of the nozzle with various nozzle throat size. Experiments and numerical simulations were also carried out for further understanding of the flow leakage effects. It was found that the nozzle stagnation pressure was diminished by the increase of the size of the nozzle throat. It was also found that the steady pressure in the stagnation were maintained well at the area ratio of the driven tube to the nozzle throat is 4.5.
Keywords
Reflected Shock Tunnel; Nozzle Throat; Reflected Pressure;
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