论文部分内容阅读
通过6英寸直径火箭发动机的静态试车,并用独特的计算机编码进行数据处理,求出了11种不同喷管型面的喷管排出效率和推力效率。确定了具有尖角和大的喉部曲率半径的普通收敛—扩散喷管的效率基准值。用小的园周槽来模拟入口斜面和出口锥的粗糙度缺陷。出口锥的冲刷用切割1.5英寸和4英寸半径的单个园周糟来模拟。入口和出口锥面的小糟对喷管排出效率和推力效率没有多大影响。出口锥面上的大园周糟使推力效率降低约4%。具有大的喉部曲率半径的潜入喷管的效率和普通喷管一样。设计低劣的喷管,其推力效率损失预计可达8%。
Through the six-inch diameter rocket engine static test, and a unique computer code for data processing, obtained 11 different nozzle profile of the nozzle discharge efficiency and thrust efficiency. The general convergence-diffuser nozzle efficiency benchmark with sharp corners and large throat radii of curvature was determined. A small circumferential groove is used to simulate the roughness defects of the inlet and outlet cones. Flushing of the exit cone is modeled by cutting a single perimeter with 1.5-inch and 4-inch radii. Small inlet and outlet cones have little effect on ejector discharge efficiency and thrust efficiency. Large concessions on the exit cone reduce thrust efficiency by about 4%. Submerged lances with a large throat radius of curvature have the same efficiency as normal lances. Poorly designed nozzles have thrust losses estimated to be up to 8%.