EXAMINATION OF THE EFFECT OF OXIDIZER / FUEL RATIO ON THRUST OF LIQUID OXYGEN / PARAFFIN FUELED HYBRID ROCKET ENGINE BY USING NUMERICAL METHOD


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Koçak D. , Özdamar A.

INTERNATIONAL ASIAN CONGRESS ON CONTEMPORARY SCIENCES-V, Nakhchivan, Azerbaijan, 1 - 02 June 2021, pp.1211-1217

  • Publication Type: Conference Paper / Full Text
  • City: Nakhchivan
  • Country: Azerbaijan
  • Page Numbers: pp.1211-1217

Abstract

Due to the cost and complexity of liquid fuel rockets, the explosion hazard and the problems of

thrust control of solid fuel rockets, it has been observed that hybrid rocket engines are preferred

recently. In addition to the advantages of hybrid rocket motors such as being safe and economical and

ease of thrust control, there are also disadvantages such as low regression rate. This disadvantage can

be overcome to some extent by using paraffin as a solid fuel. The main goal in rocket engines is to

achieve the highest thrust. Computational fluid dynamics deals with solving fluid dynamics and heat

transfer problems using numerical methods. Numerical methods are preferred to experimental method

due to they are cheap, they give fast results and they are suitable for solving problems at any scale.

The most known Computational Fluid Dynamics methods are finite difference method, finite element

method and finite volume method. Viscous models, which are mostly used when solving a problem by

numerical methods are turbulence model, laminar model and inviscid model. In this study, the effect

of viscous models on thrust of a hybrid rocket engine which has optimum geometry and using liquid

oxygen-paraffin propellant pair in literature was examined. Analysis of hybrid rocket engines for

different viscous models was performed using the Ansys Fluent Package program which using a finite

volume numerical method and the Mach number and thrust values obtained at the nozzle outlet were

compared.