Turbulent boundary layer combustion in the hybrid rocket

摘要: In this paper an effort has been made to survey recent theoretical and experimental work related several aspects of the hybrid combustion process. It found that is controlled by rate at which heat can be delivered fuel surface, rather than surface reaction rates. By assuming occurs in a turbulent boundary layer, regression equation developed. This formula based on procedures used other relatively studies transfer reacting layers. Two important factors are position flame effective gasification. A simple analysis provides estimate when layer turbulent. for Plexiglas-oxygen system, height above should approximately range 10% 20% thickness, depending operating conditions. The gasification process also discussed. nature leads one anticipate may occur fuel-rich mixture ratio. observed experimentally, model suggests means improving efficiency. proven experimentally. predicts existence location minimum special case where nonlinear ballistics problem treated approximate method. considerable confidence underlying assumptions. agrees reasonably well with data. However, much still needed clarify influence parameters equation, provide description internal under general