A theoretical investigation of heterogeneous combustion processes including radiative heat transfer and variable transport properties

A numerical study of the effects of radiative heat transfer and variable transport properties in the hybrid heterogeneous combustion rocket engine has been carried out. The flow in this rocket system is steady state chemically reacting turbulent flow in the axial and radial directions. Solid fuel reacts with liquid oxidizer which vaporizes rapidly and blows axially when introduced into the fuel tube, i.e., the combustion chamber. Heat released from the oxidizer-fuel combustion process provides the energy required to gasify more solid fuel. Once ignited, the combustion is self-sustaining.