Mason, J. R. and R. D. Southwick, "Large Liquid Rocket Engine Transient Performance Simulation System," Marshall Space Flight Center, Alabama .
 Bradford, J., A. Charania and B. S. Germain, "REDTOP-2: Rocket Engine Design Tool Featuring Engine Performance, Weight, Cost, and Reliability," 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Florida, AIAA-2004-3514.
 McBRIDE and GORDON, "Computer Program for Calculation of Complex Chemical Equilibrium Compositions, Rocket Performance, Incident and R efleaed Shocks, and Chapman-Jouguet Detonations," NASA SP-273.
 Ponomarenko, A., "RPA: Thermal Analysis of Thrust Chambers.," 2012.
Available, [on line]: "http://sierraengineering.com/ ROCCID/roccid.html," [Online].
 Davidian, K.J., "Comparison of Two Procedures for Predicting Rocket Engine Nozzle Performance," in 23rd Joint Propulsion Conference, San Diego, CA, U.S.A., AIAA-87-2071.
 Manfletti, C., "Start-Up Transient Simulation of a Pressure Fed LOx/LH2 Upper Stage Engine Using the Lumped Parameter-based MOLIERE Code," in 46th Joint Propulsion Conference & Exhibit, Nashville, 2010.
 Song, E. and J. Song, "Modeling of Kerosene Combustion Modeling of Kerosene Combustion," Advances in Mechanical Engineering, vol. 9, 2017.
 Gray, H.L. "Modelling of Combustion Processes in Small Liquid Bipropellant Thruster," in 28th Joint Propulsion Conference and Exhibit, Nashville, 1992.
 Nonnenmacher, S. and M. Piesche, "Design of Hollow Cone Pressure Swirl Nozzles to Atomize Newtonian Fluids," Chemical Engineering Science, vol. 55, no. 19, 2000, pp. 4339-4348.
 Rizk, N.K. and A.H. Lefebvre, "Internal Flow Characteristics of Simplex Swirl Atomizers," Journal of Propulsion and Power, vol. 1, no. 3, pp. 193-199, 1985.
 Kim, S., T. Khil, D. Kim and Y. Yoon, "Effect of Geometric Parameters on the Liquid Film Thickness and Air Core Formation in a Swirl Injector." Measurement Science and Technology, vol. 20, no. 1, 2008.
 Rizk, N. K. and A. H. Lefebvre, "Prediction of Velocity Coefficient and Spray Cone Angle for Simplex Swirl Atomizers," in Proceedings of the 3rd International Conference on Liquid Atomization and Spray Systems, London, 1985.
 Moongeun, H., J. Jeon and S.Y. Lee, "Discharge Coefficient of Pressure-Swirl Atomizers with Low Nozzle Opening Coefficients," Journal of Propulsion and Power , vol. 28.1, 2012, pp. 213-218.
 Jones, A. R., "Design Optimization of a Large Pressure-Jet Atomizer for Power Plant," in Proc. 2nd ICLASS, Madison, Wis., , 1982.
 Gater, R.A. M. R. L'Ecuyer and C. F. Warner, Liquid-Film Cooling It's Physical Nature and Theorical Analysis, Jet Propulsion Center,Purdue university, Indiana, 1965.
 G. P. Sutton and Biblarz, O., Rocket Propulsion Elements, 7th ed., New York: John Wiley & Sons, 2001, p. 197–240.
 S. Shine, Sunil Kumar, S. and Suresh, B. "A New Generalised Model for Liquid Film Cooling in Rocket Combustion Chambers," International Journal of Heat and Mass Transfer, vol. 55, no. 9, 2012, pp. 5065–5075.
 Stechman, R. C., J. Oberstone and J. C. Howell, "Film Cooling Design Criteria for Small Rocket Engines," 4th Propulsion Joint Specialist Conference, Cleveland, AIAA, 1968.
 Grisson, W.M., "Liquid Film Cooling in Rocket Engines," United states air force, Atlanta, Georgia, 1991.
 Gotzig, U. and E. Dargies, "Development Status of Astriums New 22N Bipropellant Thruster Family," in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, 2003.
 Preclik, D., D. Estublier and D. Wennerberg, "An Eulerian-Lagrangian Approach to Spray Combustion Modeling for Liquid Bi-Propellant Rocket Motors," in 31 st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibi, San Diego, CA, 1995.
 Soltani, M.R., K. Ghorbanian, M. Ashjaee and M. R. Morad, "Spray Characteristics of a Liquid–liquid Coaxial Swirl Atomizer at Different Mass Flow Rates," Aerospace Science and Technology, vol. 9, no. 7, 2005, pp. 592-604.
 Lefebvre, A.H. and V. G. McDonell, Atomization and Sprays, Taylor & Francis Group, 2017.
 Yang, V., M. Habiballah, J. Hulka and M. Popp, Liquid Rocket Thrust Chambers: Aspects of Modeling, Analysis, and Design, American Institute of Aeronautics and Astronautics, Inc, 2004.
 Suess, R.P. and L.B. Weckesser, "Equilibrium, Adiabatic Wall and Stagnation Temperatures at Altitudes up to 100,000 Feet and Mach Numbers up to 20," Defense Documentation Center for Scientific and Technical Information, Viginia, 1966.
 Howell, J.C., J. Oberstone and R. C. Stechman, "Design Criteria for Film Cooling for Small Liquid-propellant," Journal of Spacecraft and Rockets, vol. 6, no. 2, 1969, pp. 97-102.
 J.D. Anderson, Modern Compressible Flow: with Historical Perspective, Boston: McGraw-Hill, 2003.
 Silva Couto, H., P. T. Lacava, D. Bastos-Netto and A. P. Pimenta, "Experimental Evaluation of a Low Pressure-swirl Atomizer Applied Engineering Design Procedure," Journal of Propulsion and Power, vol. 25, no. 2, 2009, pp. 358-364.
 N. J. Labbe, Determining Detailed Reaction Kinetics for Nitrogen-and Oxygen-Containing Fuels, PhD Thesis, University of Massachusetts - Amherst, 2013.