Computational Investigation of Optimized Rocket Nozzle Profiles for Maximizing Exhaust Velocity using Python

The design of a rocket nozzle is critical in determining exhaust flow note and velocity, serving as the primary controller of gas expansion. Among various geometrics, the bell nozzle is often preformed due to its superior thrust efficiency and compact physical structure The research focuses on the optimization of bell nozzle. Configuration to achieve maximum gas exhaust velocity through computational modeling. Traditional rocket engineering and experimental testing are often resources intensive, time consuming and costly. To address these challenges, this study utilizes a Python-based simulation framework to analyze gas flow dynamics within various nozzle profiles. The results demonstrate that computation optimization can significantly enhance exhaust velocity, leading to improved fuel efficiency and overall rocket performance. This model demonstrates that even simple coding can assist students in solving complex problems within the field of space science. By utilizing computational simulations, this approach aims to improve future rocket technology and enhance the understanding of propulsion systems.