Abstract
Experimental results of $30^{\circ}-15^{\circ}$ nozzles were compared with numerically calculated convective heat transfer coefficients using FLUENT, Boundary Layer Integration Method and Bartz predictions. Also, the convective heat transfer coefficients were calculated by using FLUENT and boundary layer integration method for NASA HIPPO nozzles according to the characteristics of combustion gas and the correlation between pressure and pressure was compared. Finally, thermal analysis of NASA HIPPO nozzle was performed to compare the ablation thickness and char depth according to the combustion gas characteristics.
$30^{\circ}-15^{\circ}$ 노즐의 실험결과와 FLUENT, 경계층 적분법, Bartz 예측식을 사용하여 수치계산한 대류열전달계수를 서로 비교하였다. 또한 NASA HIPPO 노즐을 대상으로 FLUENT와 경계층 적분법을 이용하여 연소가스특성에 따른 대류열전달계수를 계산하고 압력과의 상관관계를 비교하였다. NASA HIPPO 노즐을 대상으로 열반응 해석을 실시하여 연소가스특성에 따른 삭마두께와 숯 깊이를 비교하였다.