NUMERICAL MODELING OF HTPB/O2 COMBUSTION PROCESS IN A HYBRID ROCKET MOTOR TO DETERMINE SOLID FUEL SURFACE REGRESSION RATE

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AHANGAR M.; EBRAHIMI R.; GHAFURIAN A.

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Journal: FUEL AND COMBUSTION Year:2010 | Volume:2 | Issue:2 Page(s): 25-39

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Title

NUMERICAL MODELING OF HTPB/O2 COMBUSTION PROCESS IN A HYBRID ROCKET MOTOR TO DETERMINE SOLID FUEL SURFACE REGRESSION RATE

Author(s)

AHANGAR M. | EBRAHIMI R. | GHAFURIAN A. | Issue Writer Certificate

Keywords

HYBRID ROCKET ENGINEQ3

CHEMICAL REACTING FLOWQ3

SOLID FUEL PYROLYSISQ3

REGRESSION RATEQ2

Abstract

In this study, a two-dimensional, planar, numerical solution has been used to model the chemically reactive viscous flow in hybrid rocket motors for the purpose of determining the e solid fuel REGRESSION RATE. The solution employs an implicit finite-volume, lower-upper Steger-Warming scheme (LU-SW) based on Van Leer’s flux vector splitting method together with MUSCL technique, which includes minmod flux-limiter function. In agreement with other experimental studies, C4H6 species is considered as the main gaseous product of HTPB pyrolysis. The rate of pyrolysis is described by means of an Arrhenius-type relationship. In the present work, the chemical reactions between Oxygen and C4H6 are presented through an 11–species and 20–Step chemistry model. Also, turbulence is simulated using the Baldwin-Lomax algebraic eddy viscosity model. The characteristics of reactive flow in port and nozzle such as temperature distribution, Mach number, REGRESSION RATE and surface temperature are calculated. Numerical simulation of a lab scale motor firing is presented, whereby comparison with other computational and experimental data shows good agreement between the predicted and measured REGRESSION RATE.

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APA: Copy

AHANGAR, M., EBRAHIMI, R., & GHAFURIAN, A.. (2010). NUMERICAL MODELING OF HTPB/O₂ COMBUSTION PROCESS IN A HYBRID ROCKET MOTOR TO DETERMINE SOLID FUEL SURFACE REGRESSION RATE. FUEL AND COMBUSTION, 2(2), 25-39. SID. https://sid.ir/paper/138483/en

Vancouver: Copy

AHANGAR M., EBRAHIMI R., GHAFURIAN A.. NUMERICAL MODELING OF HTPB/O₂ COMBUSTION PROCESS IN A HYBRID ROCKET MOTOR TO DETERMINE SOLID FUEL SURFACE REGRESSION RATE. FUEL AND COMBUSTION[Internet]. 2010;2(2):25-39. Available from: https://sid.ir/paper/138483/en

IEEE: Copy

M. AHANGAR, R. EBRAHIMI, and A. GHAFURIAN, “NUMERICAL MODELING OF HTPB/O₂ COMBUSTION PROCESS IN A HYBRID ROCKET MOTOR TO DETERMINE SOLID FUEL SURFACE REGRESSION RATE,” FUEL AND COMBUSTION, vol. 2, no. 2, pp. 25–39, 2010, [Online]. Available: https://sid.ir/paper/138483/en

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