An Approximate Method for Estimating the Performance of Oxygen-Oil Rockets

摘要

A method is described which enables the operating conditions of an oxygen-oil rocket to be determined to a reasonably accurate degree. Less important components such as OH, O and H are not allowed for, but the method is otherwise exact and could be extended to cover these components. Curves are given for the total heat and entropy of the constituent gases, and for the relevant equilibrium constants. These values are used to derive the total heat-entropy diagrams for four mixture ratios over a range from 1 to 60 atmospheres pressure in each case. Further curves are given which show the theoretical throat and outlet areas, and also the specific impulses for expansion down to 1 atmosphere pressure.