그라파이트 삭마 현상의 수치해석적 연구

Thermal Protection Material(TPS) is used to protect rocket structure from excessive heat from the exhaust. Because TPS is destroyed by the exhaust, determining proper amount of TPS and apply it to nozzle is important. Due to the recent restriction in the development cost, numerical simulations are usually utilized for design. In this research, relatively simple graphite is selected for study and numerical code for thermal analysis is developed. Ansys Fluent v.14 is used for flow simulation and User Defined Function(UDF) is used for code implementation. The developed code is applied to nozzle with exit mach number 3 and simulation of conduction/convection/ablation is done.