Rotational axisymmetric mean flow and damping of acoustic waves in asolid propellant rocket.

.!LTHOUGH for many purposes the one-dimensional apft proximation to the steady flow in a rocket chamber is adequate, there are occasions when more precise information is required. For example, analysis of the stability of pressure oscillations involves knowledge of the streamlines. It has been common practice to use the solution for potential flow subject to the boundary conditions of no flow through the head end and uniform speed normal to the burning surface. Since the Mach number generally is very small, one may assume the density to be constant; the result for the Mach number in a cylindrical chamber is