喷管喉部型面对发动机效率的影响

采用轴对称无粘流动模型，计算固体火箭发动机喷管喉部上，下游曲率半径和圆柱长度对发动机比冲，喉部流量和推力效率的影响，经与实验数据比较，证明该方法可行。研究结果得出喷管喉部型面应是具一定大小的上，下游曲率半径，并有一较短的圆柱段。文中提供的喉部型面参数的一般取值范围可供设计参考。

Effects of Nozzle Throat Contour on Motor Efficiency

The axisymmetric and inviscid model has been presented here to predict the influence of nozzle upstream and downstream throat radius of curvature and length of throat cylinder on the specific impule and throat mass flow rate and thrust efficiency of solid rocket motor. This method is available by comparion with experimental date. Computation results show that the nozzle throat contour should have definite upstream and downstream throat radius of curvature and a shorter throat cylinder. The range of nozzle throat contour parameters is also given for designer reference.