Solution of the problem of steady flow of a perfect gas in a straight channel with mass addition is discussed, and a typical solution is demonstrated for the case of mass ad dition at constant stagnation enthalpy. This problem is then combined with the discharge characteristics of sonic nozzles, and the solution of the combined problem is demonstrated, using a burning propellant as a mechanism of mass addition at constant enthalpy. It is shown that, when the burning characteristics of the propellant and the thermodynamic properties of the gas are established, the flow field depends upon two dimensionless geometrical variables familiar iri the internal ballistics of rocket mo tors. The discussion places particular emphasis on iden tity and dependence of ballistic variables and the nature of the problem posed by the solid propellant rocket motor.
No takes yet. Share an insight, caveat, or question.
E. W. Price (1953) studied this question.