This study aims to investigate and clarify the fundamental relationship between the burning surface area of rocket propellants and their mass as well as how this affects the burn rate and mass consumption rate. The intention is to fill a knowledge gap within the field of amateur rocketry. The goal is to develop a universally applicable model for the burn profile of rocket propellants which can be used in other studies and applications

This study investigates the relationship between surface area and mass burn rate in spherical sugar-based rocket fuel, focusing on how the fuel's geometry affects its combustion pattern. Through controlled experiments, fuel samples of varying masses and radii were produced using a mixture of potassium nitrate, sugar, and corn syrup. The burn time and linear burn rate were measured to analyze how surface area and mass influence combustion. The results show that burn time increases linearly with both mass and radius, confirming that larger fuel quantities take longer to combust. However, the linear burn rate remains nearly constant regardless of changes in size or mass, suggesting that combustion speed is primarily determined by the fuel's chemical composition rather than its physical dimensions. Additionally, mass burn rate exhibits an exponential increase with radius, highlighting the significant impact of surface area on combustion efficiency. These findings contribute to a better understanding of solid rocket fuel behavior, particularly in amateur rocketry. The study demonstrates that optimizing fuel geometry, rather than merely increasing quantity, can enhance performance and provide practical insights for designing more efficient propulsion systems.