Characterization of Fuel Regression in a Radial Flow Hybrid Rocket

Abstract

Reliable ignition and stable combustion have been achieved in a lab-scale radial-e ow hybrid rocket engine. The device utilizes 85% hydrogen peroxide and polyethylene and was tested at chamber pressures ranging from 118 to 238 psia. Fuel regression behavior was characterized with respect to initial geometry and mass e ux. The measured regression rates are greater than observed in axial port designs at the same e ux and chamber pressure levels. Although the regression behavior is effected locally by the three-dimensional e ow structure, the results were more uniform than predicted by lumped parameter ballistics approximations. For this reason, radial-e ow designs with acceptable fuel utilization appear to be feasible.