| Abstrakt: |
One of the most important components of a Hybrid Rocket Engine (HRE) is the nozzle which functions to control the rate of flow, pressure, and speed of stream distribution in the convergent-divergent nozzle. Recently, HRE has potential as a future propulsion system. In this paper, to obtain the ideal HRE expansion outlet, the geometry of the divergent angle of the nozzles had simulated. The analytical results are used to compare the Mach number, pressure and temperature measurements with aimed to found the geometry with the most ideal expansion nozzle. Computational Fluid Dynamics Analysis (CFD) analyzed various performance parameters in detail for the HRE nozzles from inlet to outlet using software Ansys Fluent. Convergent angle, throat diameter, and length of the nozzles had the same geometrical dimensions, the divergent section used 6°,9°,12°,15°,18°,21°,24°,27°,30°,33° variations of angles. After the simulation, the results showed that the highest Mach number was Mach 1.59914 at the 6° divergent angle and the lowest was Mach 0.213108 at the 33° divergent angle. The highest pressure was 437259 Pa at the 18° divergent angle and the lowest was 298470 Pa at the 6° divergent angle. The temperature fluctuated as the divergent angle increased with the highest at 2801.91 K at the 9° divergent angle and the lowest was 2326.72 K at the 15° divergent angle. Furthermore, the results revealed oblique shock shifts closer to the throat caused the Mach number decreased at the outlet as the divergent angle increased, and a change in cross-sectional diameter due to an increase of nozzle divergent angle also caused head loss minor (expansion) occur. The 6° divergent angle allows having the most ideal geometry in terms of the highest Mach number output with the lowest pressure closest to the ideal expansion. [ABSTRACT FROM AUTHOR] |
