Abstract
a one-dimensional mathematical and numerical model for the flow in a LOX/LH2-rocket engine nozzle is presented. Temperature is used as unknown at energy equation and velocity is obtained for all speeds regimes. For all analyses, tiny tolerances and a large number of iterations were used, in order to achieve the round-off error and estimate the discretization error. For each physical model, different chemical schemes are compared (among them and to reference ones, with good accuracy), indicating the influence of the choice of such schemes on numerical results. Six-species models and 80 control volumes are recommended, at least, for preliminary tests. 1 Nomenclature
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
