Af terburning Predictions for Metal-Modified Propellant Motor Exhausts

Predicted extents of afterburning in fuel-rich exhausts of metal-modified, double base propellant rocket motors have been investigated by means of a plume prediction code, which incorporates fully coupled turbulent kinetic energy boundary-layer and nonequilibrium chemical reaction schemes. The influences of a number of metals, including potassium, iron, molybdenum, tungsten, barium, tin, and chromium, on afterburning have been examined for a 300 N thrust motor. The effects of changes in total effluent mass flow rate and exit temperature were determined for both modified and unmodified propellants under static and flight conditions at sea level.