In this research, the design of a cooling system for the combustion chamber of a ramjet engine and the effect of various cooling methods on the temperature distribution of the combustion chamber wall have been addressed. The components of the ramjet engine, types of ramjet engine combustion chambers, and the governing thermodynamics of the ramjet engine components have been studied. After determining the engine operating conditions using thermodynamic relations, the inlet conditions of the combustion chamber were specified. Following the determination of the flow conditions in the combustion chamber using existing empirical relations, the necessity and effect of film cooling were investigated. The numerical solution was validated with obtained experimental results. Using the numerical solution, film cooling methods with a simple gap, spray cooling, and a punched ring were examined. Various cases were studied by changing the geometry dimensions of the lip and the cooling gap size in spray cooling for a single cooling ring, and the required bypass air flow rate was investigated. Then, for a punched ring, the cooling effect was studied by changing the inlet flow angle and incorporating a lip. Spray cooling yields favorable results when the ratio of the lip height to the gap size is equal to or greater than one. The punched ring with a lip and angles close to 90 degrees provides favorable results.