喷管激波贴口压比计算

本文根据试验数据,利用多元线性回归分析方法建立了轴对称收敛—扩散喷管激波贴口时落压比与面积比,收敛半角,扩张半角,无量纲喉道曲率半径之间关系的数学模型。计算结果为喷管试验研究和跨音速流计算提供了依据。 

CALCULATION OF PRESSURE RATIO AT NOZZLE EXIT WITH SHOCK

A mathematical model of a axisymmetric convergent-divengent nozzle isset up by multivariant linear regression analysis method. The relationships of pressure ratio at nozzle exit with shock to four geometric parameters, i. e. area ratio, half-convergent angle, half-divergent angle and radius ratio of throat curvature to throat, are considered. The pressure ratio only depends on the area ratio. Other parameters have little effect on it. The results provide the basis for testing and transonic calculation of the axsiymmetric convergent-divergent nozzle.