Testing and performance analysis of a rocket’s hybrid propulsion system using various types of nozzles
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Abstract
At present, the development of rocket propulsion systems must concern characteristics of efficiency, safety, environmental friendliness, economics, and the ability to control the on and off of combustion. Therefore, researchers and engineers search for alternative technologies by applying theory in practice, which has resulted in compulsive innovations and hybrid propulsion systems of rockets. It is unique because it incorporates the advantages of solid and liquid fuels. Hybrid propulsion systems are a consolidation of a liquid oxidizer and a solid fuel. This research focused on testing and analyzing the performance of a rocket's hybrid propulsion system using different types of nozzles. The study involved the design and construction of ten different types of nozzles, divided into 4 grouped as follows: 1) conical inlet and outlet with different outlet diameters, impacting nozzle length, 2) cone-shaped inlet and outlet with varying throat diameters affecting airflow cross-sectional area, 3) cone-shaped inlet and curved outlet affecting airflow characteristics at the exit and 4) inlet and outlet angles of different sizes impact the nozzle angle slope with the reynolds number less than 1×104. The test results showed that group 1 thrust force had the highest thrust, and the highest specific impulse value belonged to group 3.
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