Semi cryogenic Engine is designed for high thrust level condition which works in Oxidizer Rich Staged Combustion Cycle (ORSCC) with a propellant combination of Liquid Oxygen (LOX) and Kerosene. The thrust chamber – the propulsion unit – of the engine is provided with multiple number of coaxial swirl injector elements arranged in concentric circles on the injector face plate. To characterize the injector element, a single coaxial element is chosen and an ablative cooled combustion chamber is designed for it by keeping the fundamental chamber parameters. Transient thermal analysis of Silica phenolic lined chamber for the selected Chamber pressure and mixture ratio condition is carried out prior to hot test. Hot test is successfully completed and the results are compared with the predictions along with identifying future course of experiments.