Experimental studies on liquid film cooling of rocket motors - (Phase II)

An experimental study of liquid film cooling with tangential injection of 2-D liquid film along a polished surface of a square duct with co-flowing hot combustion gases is described. Experiments are carried out for a range of hot gas conditions, namely, velocity 60 to 120 mis,temperature 3500e to 500oe, pressure 1 to 2 atmospheres and coolant flow 0.02 to 0.12 litres/min. A simple heat transfer analysis is carried out to predict the liquid fi1m cooled length and they are compared with the experimental data