• BHIRENDRA KUMAR
• SUDHIR SINGH RAJPUT

Thermodynamic processes inside a nozzle provide the mathematical tools needed to calculate the performance of a rocket propulsion system and identify numerous critical design parameters. They're useful for evaluating and comparing the performance of different rocket systems; they allow for the prediction of the operating performance of any rocket unit that uses thermodynamic gas expansion, as well as the need to determine several design parameters for any given performance requirement. This principle applies to any propulsion system that uses the expansion of a gas as a propellant for ejecting matter at high speeds. The main goal of this research is to determine the location and strength of the normal shock wave in the divergent portion of the nozzle, as well as to investigate the nozzle's performance and flow characteristics under various operating conditions and with various nozzle geometry, because this shock degrades the nozzle's thrust producing performance. The limiting pressure ratio at which the nozzle just runs full has been estimated using an empirical expression, and charts have been given from which the shock position inside the nozzle may be determined.

CFD (computational fluid dynamic), CVM (control volume method), DC nozzle (divergent convergent nozzle)

"Comparative Analysis of Flow Characteristics of De Laval Nozzle", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.9, Issue 6, page no.h624-h629, June-2022, Available :http://www.jetir.org/papers/JETIR2206770.pdf

"Comparative Analysis of Flow Characteristics of De Laval Nozzle", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.9, Issue 6, page no. pph624-h629, June-2022, Available at : http://www.jetir.org/papers/JETIR2206770.pdf