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palizvani, M., Jamali-, -. (2024). Numerical investigation of the effect of the injector characteristics on the specific impulse, thrust, and chamber pressure of a hybrid rocket motor. Electronic and Cyber Defense, 13(2), 125-144.
mohammad reza palizvani; -Ali Akbar Jamali-. "Numerical investigation of the effect of the injector characteristics on the specific impulse, thrust, and chamber pressure of a hybrid rocket motor". Electronic and Cyber Defense, 13, 2, 2024, 125-144.
palizvani, M., Jamali-, -. (2024). 'Numerical investigation of the effect of the injector characteristics on the specific impulse, thrust, and chamber pressure of a hybrid rocket motor', Electronic and Cyber Defense, 13(2), pp. 125-144.
palizvani, M., Jamali-, -. Numerical investigation of the effect of the injector characteristics on the specific impulse, thrust, and chamber pressure of a hybrid rocket motor. Electronic and Cyber Defense, 2024; 13(2): 125-144.

Numerical investigation of the effect of the injector characteristics on the specific impulse, thrust, and chamber pressure of a hybrid rocket motor

مکانیک سیالات و آیرودینامیک
Article 10, Volume 13, Issue 2 - Serial Number 33, November 2024, Pages 125-144    PDF (3.51 M)
Document Type: Original Article
Authors
mohammad reza palizvani1; -Ali Akbar Jamali-* 2
1Master's student, Imam Hossein University, Tehran, Iran
2Assistant Professor, Imam Hossein University, Tehran, Iran
Receive Date: 28 May 2024,  Revise Date: 01 October 2024,  Accept Date: 12 November 2024 
Abstract
To address the low regression rate issue of hybrid propulsion systems utilizing fuel-rich (solid) paraffin combustion, dinitrogen oxide is employed as an oxidizer. This study focuses on a computational domain that includes a combustion chamber coupled with a peripheral exit region. A three-dimensional steady-state simulation is conducted using the Reynolds-Averaged Navier-Stokes (RANS) approach, incorporating the standard k-ε turbulence model along with the Eddy Dissipation Model (EDM) to account for turbulence-chemistry interaction (TCI). A structured and uniform mesh is utilized for the oxidizer and gaseous fuel flow. The simulation results are validated against experimental data. The findings indicate that by increasing the injector diameter by 35.71% and the O/F ratio by 27.76%, the average combustion chamber pressure rises by 37.61%, the average thrust increases by 51.46%, and the specific impulse improves by 19.41% in the three-dimensional simulation. Additional simulation results demonstrate promising outcomes, and a numerical analysis is conducted to compare the effects of injector orifice diameter, oxidizer (dinitrogen oxide) injection arrangement, fuel mass fraction, and O/F ratio on the combustion chamber pressure and hybrid rocket thrust.
Keywords
Simulation and modeling; Hybrid rocket engine; paraffin; Injector effects; trust
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