Book Description

An experimental investigation was conducted to examine the flow field within the chamber of a spinning, cold flow rocket motor and to determine the effects of the interaction of this swirling flow with the decreasing area of a converging nozzle. The investigation was divided into two phases: (a) the measurement of the static pressure and velocity profiles within the chamber of the cold flow motor with a five-port impact tube probe and (b) the measurement of the effect of the swirling flow-nozzle interaction on the mass flow rate through the nozzle. The static pressure and velocity profiles were measured at two axial locations within the chamber of a simulated end-burning rocket motor for rotational speeds of 1000, 3000 and 5000 rpm. The measured axial and tangential velocity profiles ere compared with the predicted profiles, which were based upon a solid-body vortex with a uniform axial velocity. (Author).