A semi-empirical model for heat transfer and flame spreading in slotted rocket motors

This paper presents analytical and experimental results for the cold'flow aerothermodynamics of the headend star slot region of the Space Shuttle SRM. Particular attention is paid to determination of the heat transfer from the developing igniter flow to the propellant grain (slot wall), Igniter geometries considered include a single port configuration with flow along the axis of the motor (present Shuttle configuration) and a multi-port, 45" canted nozzle configuration which is similar (but not identical) to the proposed ASRM igniter geometry.