Three-Dimensional Solid Rocket Motor Internal Ballistics With a Free-Vortex Method

A novel method is developed to solve the internal flow field of solid rocket motors using free vortex elements. The goal of this work is to produce an efficient flow solver suitable for conceptual and preliminary design of solid rocket motors. The solid rocket motor is modeled as a paneled surface that represents the burning surface of the propellant in the combustion chamber. Vorticity is shed from the surface into vortex elements that flow freely through the internal domain. Results are provided for a cylindrical solid rocket motor, and the solution is compared with an analytical model. Good agreement is observed between the vortex method and the analytical solution. Internal flow solutions are obtained on the order of minutes.