Modeling conjugate heat transfer in packets of small-size planar gas-dynamic cooled nozzles

A complex physicomathematical formulation and method of solving conjugate heat transfer between viscous gas-dynamic and hydraulic flows in packets of planar cooled rocket microthrusters used for the control for spacecrafts and pumping of gas-dynamic lasers are presented. The feature of such thrusters is their small size, as a consequence of which the body rapidly warms up and needs special ways of cooling. The immersion technique is proposed for solving heat transfer problems in multiply connected domains which are inherent to cooled microthrusters. It is shown that the cooler removes a considerable amount of heat, especially in the region of the critical cross section of the nozzle.