Abstract
The goal of this current research was de termination and optimization of the Rocket Based Combined Cycle (RBCC) Engine inlet/ejector performance trend. For this purposes, a two dimensional rocket -ejector system was studied over a matrix of engine design variables. By pass ratio, ejector compressi on ratio and ejector/mixture thrust efficiency was used to analyze RBCC internal flow path physics. The primary thruster exit flow properties were calculated with the Reacting and Multiphase Program, which was used as fixed inlet conditions for the ejector /mixer analysis. The computational fluid dynamics (CFD) simulations of the inlet/ejector system were carried out with Finite Difference Navier Stokes (FDNS) code. The GO 2/GH 2 combustion physics were solved finite rate with a system of seven species and nin e reactions. The desirability approach of optimization, tied with response surface and neural networks technique has been used for response surface generation and inlet/ejector optimization. An optimum primary thruster size, duct length -to -diameter ratio and ramjet burner to ejector/mixer inlet area ratio are obtained. From this study, it is also noticed that using smaller primary rockets are more effective in reducing the mixing length.
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