Abstract
Abstract: The wind tunnel forms important aspect of testing of bodies or space vehicle. In the present study Mach 8 nozzle for hypersonic wind tunnel is thermally analysed. The analysis is formed under high temperature conditions as expected in space. The material of nozzle has been tested for high temperature with and without throat cooling conditions. The analysis is performed for alternative cycle of heating and cooling of nozzle. It was found for the conditions of analysis, the temperatures in the material of nozzle are within the acceptable limits.
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Schedule a callMore From: International Journal for Research in Applied Science and Engineering Technology
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