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The nozzle of the rocket is one of the most crucial parts for creating thrust. Many researchers are working on the different types of rocket nozzle to achieve the optimum thrust efficiency. In this research, CFD simulation was carried out. A 2D convergent-divergent nozzle was made in the FLUENT, further, a parametric setup was carried out. In this setup, a total of 47 design points were created keeping the inlet and outlet length of the nozzle as variable. To obtain the correlation between the design point length and the functional parameters like temperature, pressure, and velocity a heatmap was created. In the result, it was found that when the nozzle inlet and outlet angle are near 45 degrees and the pressure at both ends maintains an equal ratio, the nozzle provides the optimum thrust.

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Optimizing Rocket Propulsion Efficiency Through CFD Simulation of Nozzle Designs

  • 会议论文

  • 发表日期：

    2026年

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  • Veer Shukla,
  • Reetu Jain

摘要

The nozzle of the rocket is one of the most crucial parts for creating thrust. Many researchers are working on the different types of rocket nozzle to achieve the optimum thrust efficiency. In this research, CFD simulation was carried out. A 2D convergent-divergent nozzle was made in the FLUENT, further, a parametric setup was carried out. In this setup, a total of 47 design points were created keeping the inlet and outlet length of the nozzle as variable. To obtain the correlation between the design point length and the functional parameters like temperature, pressure, and velocity a heatmap was created. In the result, it was found that when the nozzle inlet and outlet angle are near 45 degrees and the pressure at both ends maintains an equal ratio, the nozzle provides the optimum thrust.