John E. Dalgleish, Adelbert O. Tischler
Experiments have been conducted with a jacketed rocket combustion chamber that was fabricated by hydraulic forming from sheet metal. Rocket combustion chambers made by this method have been used successfully. Runs with these combustion chambers have been made at over-all heat-transfer rates of 2.5 Btu per square inch per second with water cooling and also the ammonia as a regenerative coolant.
An Adobe Acrobat (PDF) file of the entire report: