Andrew E. Abramson
An investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine was undertaken. The experiments covered a range of oxidant-fuel ratios with the combustion-chamber pressure varying from 220 to 275 pounds per square inch absolute. Water and anhydrous liquid ammonia were used as coolant with the coolant flow constituting from about 12 to 25 percent of the total flow.
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