Abstract
An advance propelling nozzle is designed in a different field of applications to accelerate the fluid from subsonic to supersonic/hypersonic. It regulates the flow properties of the liquid and provides the required thrust at a given design and operating conditions. The present study describes and evaluates geometry and its flow properties locally, along with the length of the nozzle. The developed 1-D gas dynamic equations with the real gas equation for the computation of geometry and flow properties assume that the momentum rate is constant. The constant rate of momentum change theory (CRMC) with frictional effect helps in the computation of nozzle coordinates with similar flow properties at any distance (say 0.5 mm in the present case). The results obtained have been validated by computational fluid dynamic (CFD) using ANSYS 14.0. The numerical results are in good agreement in comparison with modern CRMC theory at design conditions.
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