|This thesis seeks to advance the state of the art for conceptual and preliminary design of
solid propellant rocket motors by adapting surface vorticity solution methods to the internal
ballistics problem. The practical approach is to adapt a surface-vorticity solver known as
FlightStream® originally designed for external flow analysis to the solution of internal flows of
interest to the solid rocket motor design community. This work focuses particularly on solid
propellant rocket motor combustion chambers. Four analytic models were derived and used to
validate various simple solid rocket motor internal flow models. Excellent agreement between
the analytic solutions and FlightStream® was observed. The Space Shuttle’s Reusable Solid
Rocket Motor (RSRM) was used as a more complex and realistic validation case. To compare
with the validation data, corrections to FlightStream®’s potential solution were necessary.
Analyses were conducted to ensure FlightStream® produced a valid potential solution for the
RSRM. The corrected solution was accurate to the validation data, though error increases in the
second half of the RSRM. This was believed to be due to the radial slots between the RSRM
segments, which likely generate recirculation that could not be accurately captured in the method
applied in this report.