Abstract: A rocket engine combustion chamber liner of the present disclosure has a combustion chamber in which fuel and oxygen are ignited thereby generating low-velocity gases. The rocket engine combustion chamber liner further has a throat integral with and in fluid communication with the combustion chamber that generates high-velocity gases from the low-velocity gases received from the combustion chamber. Additionally, the rocket engine combustion chamber has a nozzle integral with and in fluid communication with the throat through which the high-velocity gases are emitted causing thrust for a rocket. The combustion chamber, the throat, and the nozzle have a common outer surface and etched into the outer surface are a plurality of channels wherein the channels have the same width and depth.