RX-320 Rocket Static Pressure Combustion Chamber Prediction and Validation by Using Invers Method

Sofyan Sofyan, Vicky Wuwung

Abstract

The static pressure data of the combustion chamber which can generally be obtained by performing direct measurements when static test is performed on the rocket is an important parameter in predicting the thrust and design of the combustion chamber of the rocket. However, there is a model rocket for flight test that is used in static test. Thus, there is no mounting for static pressure sensors (for measurement) are made. To solve the problem, then the inverse method is used as an iterative solution for the basic equations of the rocket thrust force in the nozzle by guessing the value of the static pressure of the combustion chamber firstly and calculate the iteration by including the value of the rocket thrust from static test data and the efficiency variation of the nozzle. The results of this calculation are then validated by using a 3D-CFD numerical simulation to obtain a more detailed comparison on the nozzle. In this research RX 320 LAPAN rocket nozzle with focus on maximum static thrust data of static test results is used. The 3-D numerical simulation is performed using Numeca CFD software, with k-extended wall extended turbulent model, numerical multigrid level 3 scheme, center based, and convergence criteria of 10 e-05. The result of calculation by inverse method and its comparison with numerical simulation shows that the smallest difference of the combustion chamber static pressure between inverse method and numerical simulation is 0.017%, that is achieved at 92% nozzle efficiency. At this point, the static pressure of the combustion chamber is 57.94 bar. From this point of view, the results of this comparison indicate that the inverse method can be used accurately for static pressure of the combustion chamber prediction, if the nozzle efficiency is given correctly. Furthermore, with given static pressure of the combustion chamber correctly, it will be very helpful in the design of the more optimum combustion chamber.

Keywords

static pressure, combustion chamber, invers method, static test; CFD Numeca; Nozzle efficiency; RX-320

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References

A. Balabel, A.M. Hegab, M. Nasr, Samy M. El-Behery, 2011, Assessment of turbulence modeling for gas flow in two-dimensional convergent–divergent rocket nozzle, Journal of Applied Mathematical Modelling No.35 p 3408-3422

A.Shanthi Swaroopini, M.Ganesh Kumar, T.Naveen Kumar, 2015, Numerical Simulation and Optimization of High Performance Supersonic Nozzle at Different Conical Angles, International Journal of Research in Engineering and Technology (IJRET), Volume: 04 Issue: 09

Barrere, Marcel, 1960, Rocket Propulsion, Elsevier Publishing Company

Bogdan-Alexandru Belega, Trung Duc Nguyen, 2015, Analysis of Flow in Convergent-Divergent Rocket Engine Nozzle Using Computational Fluid Dynamics, International Conference of Scientific Paper

F.Algimantas, Račkauskas. Saulius, Survila. Arvydas, Patašienė. Laima; 2015, Design of the testing system for solid propellant rocket motor thrust measurements using mathematical modelling techniques, Journal of Measurements in Engineering, Volume 3, Issue

2015,http://www.nerorockets.org/nero/neh-projects.htm

Huh. Hwanil, Kim. Jungyong, Kim. Yo, Driscoll. F. James; 2002, Assessment of Thrust from Pressure Measerements,38thAIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Indianapolis, Indiana.

Nnali-uroh, E., Oyedeko, K.F., Anyaba, Prince, 2016, Prediction of Instantaneous Burning Rate of Solid Propellant for a Solid Rocket Motor, International Journal of Scientific Engineering and Applied Science (IJSEAS)

Numeca User Manual, 2015, Fine Open User Manual, Numeca International.

Patel, Malay S, Mane, Sulochan D., Raman, Manikant, 2016, Concepts and CFD Analysis of De-Laval Nozzle, International Journal of Mechanical Engineering and Technology (IJMET)

Sutton, George P., Biblarz, Oscar, 2016, Rocket Propulsion Elements 9th Edition, Wiley

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