• TANMOY SAHA
• AYUSH GOYAL
• NIKHIL GANGAMKOTE

Rocket propulsion systems in aerospace require the basic component of convergent-divergent (CD) nozzles. Exhaust gas supersonics is the main operational objective of this device. The convergent section compresses flow to Mach 1 level at the throat while the divergent section uses expansion to boost exit velocities of the material. This design functionally enhances thrust generation by reducing shock wave losses while delivering better thermal resistance properties thus ensuring smooth flow expansion. Defence operations and space launch vehicles use CD nozzles because they ensure stable supersonic flow during all operational phases. Numerical analyses conducted for a CD nozzle having Mach 3 speed produce this research's key results about both aerodynamic behaviour and thermal response. The nozzle modelling process used CATIA V5 while ANSYS Fluent performed the CFD simulations. The model operated at 20-kilometers of altitude using 15-MPa chamber pressure together with an exit ambient pressure of 5529 Pa. The analysis achieved results for flow parameters such as temperature and pressure and velocity. This study verified efficient supersonic expansion that occurred with minimal shock interactions along with achieving the maximum possible pressure recovery. A temperature distribution assessment confirmed that extreme environmental conditions do not damage the nozzle design. The findings demonstrate the nozzle’s aerodynamic efficiency and its feasibility for high-speed propulsion applications. Future work may involve optimizing nozzle contouring, implementing altitude-adaptive designs, and exploring advanced materials to further enhance performance and durability in extreme aerospace environments.

CFD analysis of a Mach 3 CD rocket nozzle for supersonic flow, thrust optimization, and shock wave control.

"Shaping Supersonic Flow: Numerical Insights into a Mach 3 Rocket Nozzle", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.12, Issue 2, page no.c713-c725, February-2025, Available :http://www.jetir.org/papers/JETIR2502283.pdf

"Shaping Supersonic Flow: Numerical Insights into a Mach 3 Rocket Nozzle", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.12, Issue 2, page no. ppc713-c725, February-2025, Available at : http://www.jetir.org/papers/JETIR2502283.pdf