Shock waves for a converging-diverging nozzle and for a rocket

The project is about studying the whole rocket. The work is based on comparing between analytical and theory results on the converging diverging (C-D) nozzle, also called the Laval nozzle for an isentropic flow, a normal shock wave in the diverging section, an oblique shock wave and an expansion at the exit. Then a simulation of the flow at the upper surface of the rocket by CFD will be made, considering the upper area as diamond shaped. The aim of the simulation is to show the oblique shock wave created by supersonic speed and doesn’t intersect with the rest of the rocket, reducing overall the drag

本课题旨在全面研究火箭。研究工作基于对等熵流下的收敛扩散（C-D）喷管，亦称拉瓦尔喷管，以及扩散段中的正激波、斜激波以及出口处的膨胀的解析和理论结果的比较。随后，将通过计算流体动力学（CFD）模拟火箭上表面的气流，将上表面区域视为菱形。模拟的目的是展示由超声速产生的斜激波，并确保其不与火箭的其他部分相交，从而降低整体阻力。