A COMPARISON BETWEEN FLOWS OF THREE REACTION SYSTEMS THROUGH SUPERSONIC PROPULSIVE NOZZLES | ||
| The International Conference on Applied Mechanics and Mechanical Engineering | ||
| Article 41, Volume 13, 13th International Conference on Applied Mechanics and Mechanical Engineering., May 2008, Pages 158-175 PDF (1.72 M) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/amme.2008.39262 | ||
| Authors | ||
| KEMRY M. M.1; EL-KADY E.A. A.2 | ||
| 1Prof., Mechanical Engineering Department, Al-Azhar University, Cairo, Egypt. | ||
| 2Associate Prof. , Mechanical Engineering Department, Al-Azhar University, Cairo, Egypt. | ||
| Abstract | ||
| ABSTRACT The present study is concerned with the analytical solution of frozen flows of combustion gases through the supersonic region of an axisymmetric nozzle. The product gases of C12H26–O2 , H2–O2 and H2–F2 reaction systems are considered. A predictor-corrector method is employed for approximating the differential terms of the governing equations; while the method of characteristics is used to solve the resulting equations for variable specific heat ratio. The study includes a comparison of the results of the three reaction systems. The results involve the flow field parameters; namely , the temperature T, the pressure P, the velocity V and Mach number M. The results of the propulsion Parameters namely; thrust force F, the specific impulse Isp, specific impulse based on fuel combustion Isp,f and thrust efficiency ηf are also presented. All results are presented for a combustion chamber dimensionless pressure , Pc=30 , an equivalence ratio, Φ=1, a dimensionless throat radius of curvature of the nozzle, ρt=2 , and a straight nozzle wall angle, ψ=20°, as a controlling factors. Results show that the point of tangency at nozzle wall is a source of creating oblique shock waves. The C12H26–O2 , H2–O2 reaction systems produce approximately equal thrusts which are higher than that produced by H2–F2 reaction system. Besides, the specific impulse attained by H2–F2 system is of highest magnitude; and there are negligible influences of the three systems on the thrust efficiency. | ||
| Keywords | ||
| Frozen flow of combustion gases – Characteristic lines – Method of characteristics – Initial and boundary value problems – Supersonic flow – Thrust force – Specific impulse – Thrust efficiency | ||
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