Analysis of hybrid rocket combustion

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Analysis of hybrid rocket combustion

Cherng, D.L. / Tao, C.C.

AbstractThe problem involving flow of a turbulent boundary layer with mass injection and combustion is studied to investigate the hydrid rocket combustion. Because of the presence of combustion, the momentum equation is coupled to the energy and species equations. Particular attention is given in this paper to determine the eddy viscosity, and a combined model for it is proposed as follows: (1) the Cebeci's model for eddy viscosity is modified to allow for mass injection and combustion in the inner region; (2) for the eddy viscosity in the outer region of boundary layer, the Wilcox-Traci's two-equation model is effectively applied.The turbulent boundary layer equations are solved numerically in a finite-difference method developed by Patankar and Spalding. The input data are taken from Jones. According to the proposed model, the distribution of the viscosity parameter is obtained and similar in shape to Jones' data.Therefore, the proposed combined model of eddy viscosity has been developed to the stage where it can be used to predict quantitatively the behavior of compressible turbulent boundary layer with mass injection and combustion. However, the discrepancy between prediction and experimental data still exists, which may be due to the flame sheet assumption. Further investigation is needed to improve the prediction.