In this project work i am going to design a supersonic flow Convergent-Divergent nozzle from basic values of assumptions. It is designed for Mach 2.5, the shock wave that affects flow performance of nozzle from NPR value 1.52 (Nozzle pressure ratio i.e., the ratio between exit pressure of the nozzle to ambient pressure) according to the early studies. So in my work, thermal analysis of nozzle will be done using commercial CFD software for various NPR from 1.50 to 1.63. This range is chosen because shock wave is formed at 1.52 and nozzle is chocked at 1.63 which is reported. Thus this study is to check whether the shock wave gets changing with any other characterises and the influence over each other.
|Number of pages||4|
|Journal||International Journal of Applied Engineering Research|
|Issue number||45 Special Issue|
|Publication status||Published - 01-01-2015|
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