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During design process of a bipropellant rocket engine one of the most important problems is to assume proper combustion conditions. In the preliminary design, simple NASA CEA application can be used, which 0D model for calculating combustion parameters and creating initial geometry of the engine were applied. This combustion model gives values of the thermodynamic parameters and composition of the exhaust gases in few specific cross sections but this information is not full, especially across combustion chamber. The CFD 2D or 3D analysis provide information about all parameters in every point in the combustion chamber and the nozzle, so there is possibility to predict in better way dimensions of combustion chamber and also can be used for optimization of the injection process. In the paper were performed calculations of Jet-A – Oxygen mixture for bipropellant rocket engine in NASA CEA code. Most important dimensions for preliminary design of geometry of the engine was obtain. Additional analysis were performed in ANSYS FLUENT for choose proper length of the combustion chamber which guarantee stable combustion process. Keywords: numerical calculation, combustion modeling, rocket engine, CEA, Ansys Fluent