A convergent-divergent (CD) nozzle plays a critical role in rocket propulsion by converting thermal energy into kinetic energy to generate thrust. In this work, a conical CD nozzle is designed and analyzed using CFD and structural simulations. The nozzle is modeled in CATIA and analyzed using ANSYS under operating conditions of inlet pressure 300 psi and outlet pressure 14.7 psi. The results show supersonic flow generation with Mach number reaching 2.57 at the exit. Structural analysis indicates safe stress levels with minimal deformation. Analytical and simulation results are found to be in close agreement, validating the design approach.

A convergent–divergent nozzle was successfully designed and analyzed using CFD and structural methods. The results confirm that the nozzle efficiently converts thermal energy into kinetic energy, achieving supersonic flow at the exit. Structural analysis indicates that the design is safe under given operating conditions with minimal deformation. The comparison between analytical and simulation results shows good agreement. This study demonstrates that CFD tools are effective for predicting nozzle performance and can be used for further optimization in aerospace applications.

K. M. Pandey, S. K. Yadav, “CFD Analysis of Rocket Nozzle,” 2010 K. P. S. Surya Narayana, “Simulation of CD Nozzle,” 2016 Gelu Solomon, “Design and Analysis of Rocket Nozzle,” 2020 R. Hari Krishnan, “Optimized Nozzle Design,” 2020 Shaik Muzib, “Solid Propellant Nozzle Design,” 2019 Dr. Cemil Kortleve, “Supersonic Nozzle Design,” 2022 Preet Baxi et al., “Bell Nozzle CFD Analysis,” 2021 P. Chinmai et al., “Nozzle Performance Study,” 2018

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