Abstract
A coupled approach is adopted to solve the conjugate problem of fluid flow and heat transfer in solid rocket nozzles in order to achieve an optimum thermal protection system (TPS). The computational fluid dynamics (CFD) code to solve the Navier-Stokes equations for fluid flow in a rocket nozzle is coupled with the charring material ablation code through an energy balance at the active surface of the wall material. The present analysis compares well with the test results generated in-house as well as those reported in the literature.
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