Solutions are presented for the problem of gas flow in a solid propellant rocket motor using combined numerical and graphical methods. The character of the problem, sources of information, and method of solution are described, and solutions for the case of JPN ballistite propellant are presented. These solutions give the equilibrium distributions of pressure, density, velocity, and temperature of the gas stream and burning rate of the solid propellant as functions of two characteristic parameters &bgr; andJ. These parameters are descriptive of the charge geometry and flow channel geometry, respectively. The solutions cover the entire range of nozzle, charge‐size combinations, including the case of no nozzle.