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

本项目以完整火箭为研究对象。研究工作首先针对收敛扩张（C-D）喷管（又称拉瓦尔喷管（Laval Nozzle）），对比其在等熵流动（isentropic flow）、扩张段正激波（normal shock wave）、斜激波（oblique shock wave）以及出口膨胀波（expansion wave）四种工况下的解析解与理论结果；随后将采用计算流体动力学（Computational Fluid Dynamics, CFD）开展火箭上表面流场的仿真模拟，并将该上表面区域设定为菱形。本次仿真的目标为展示由超音速流动产生且不会与火箭其余结构相交的斜激波，以此降低整体气动阻力。