Novel Circular Arc Contour Design for Optimizing Rocket Nozzle Efficiency

This research introduces a method for supersonic nozzle contour design utilizing arc, termed the "T-ARC" nozzle. Numerical investigations were conducted to explore the feasibility of arc-based contours in rocket nozzle design, comparing the T-ARC design to the conical nozzle "T-CON" in terms of performance. The nozzles were truncated to achieve optimal lengths, leading to notable weight and space savings in practical applications. Three key performance measures thrust, thrust coefficient, and specific impulse at the nozzle exit Mach number were considered for the comparative analysis. The study reveals that the T-ARC design outperforms the T-CON design, demonstrating a 4.93% increase in predicted Mach number, a 10.96% boost in specific impulse, a 10.62% rise in thrust coefficient, and a 10.95% increase in generated thrust. Despite the initial challenge posed by the T-ARC's length, truncation successfully addressed this issue without compromising performance. The study suggests that the arc-based approach offers a promising alternative for supersonic nozzle design, showcasing potential benefits in terms of size, efficiency, and stability. This research not only presents a novel nozzle design surpassing the performance of traditional models but also optimizes its length, resulting in a lighter and shorter nozzle with the potential for significantly improved engineering applications.