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An experimental and computational investigation of supersonic film cooling   (SFC) was conducted on a subscale model of a rocket engine nozzle. A   computational model of a convergent-divergent nozzle was generated,   incorporating a secondary injection module for film cooling in the divergent   section. Computational Fluid Dynamic (CFD) simulations were run on the model   and different injection configurations were analyzed. The CFD simulations   also analyzed the parameters that influence film cooling effectiveness.   Subsequent to the CFD analysis and literature survey an angled injection   configuration was found to be more effective, therefore the hardware was   fabricated for the same. The fabricated nozzle was later fixed to an   Air-Kerosene combustor and numerous sets of experiments were conducted in   order to ascertain the effect on film cooling on the nozzle wall. The film   coolant employed was gaseous Nitrogen. The results showed substantial cooling   along the walls and a considerable reduction in heat transfer from the   combustion gas to the wall of the nozzle. Finally the computational model was   validated using the experimental results. There was fairly good agreement   between the predicted nozzle wall temperature and the value obtained through   experiments

Computational and experimental study on supersonic film cooling for liquid rocket nozzle applications