The objective of this project is to gain an understanding of the aerospike nozzle and to improve its development. Additionally, the project aims to investigate the limitations of current Aerospike engines and to explore potential solutions to overcome these limitations. Traditional rocket nozzles work by expanding hot gases through a converging–diverging nozzle, which creates a super-sonic exhaust stream that generates thrust. However, this design has limitations in terms of its efficiency and ability to operate at different altitudes. An aerospike nozzle, on the other hand, has a unique shape that allows it to operate more efficiently than traditional rocket nozzles. It features a spike-shaped protrusion that extends into the exhaust plume, which acts as an “invisible” nozzle extension. The spike compresses the exhaust gases at lower altitudes, allowing the nozzle to expand the gases more efficiently at higher altitudes. This design allows the rocket engine to maintain high levels of thrust over a wider range of altitudes and velocities, making it more versatile and efficient. In summary, aerospike nozzles are needed because they provide a more efficient and versatile alternative to traditional rocket nozzles, allowing rockets to perform better in a wider range of operating conditions.