Base heat flux calculation along variable pressure ratio and base temperature condition on launch vehicle

압력 조건과 기저 온도 조건에 따른 기저 열단전단률 계산

Numerical study was conducted to simulate the heat transfer on the real launch vehicle base. Three different base temperatures were chosen, to simulate the heat accumulation on the base. Moreover, six different pressure ratio conditions were used to express the different air conditions. As a result, the table that can used to estimate the base heat fox along the base temperature and pressure condition was made.