transonic nozzle

Transonic vibration induced by mismatching between engine and thrust nozzle

发动机和尾喷管匹配引起的跨音振动

The time-dependent method is applied to the calculation of transonic nozzle flow in this paper.

本文用时间相关法求解定常跨声速喷管流场。

In this paper, the time-dependent method is applied to the numerical computation of transonic nozzle flows by using of conservation and nonconservation governing equations.

用时间相关法数值计算跨音速喷管流动时，其控制方程分别采用守恒型和非守恒型方程。

The computation of transonic nozzle flow-field by a time-dependent method

用时间相关法计算喷管跨声速流场

The chamber-nozzle subsonic-transonic flowfield of solid rocket motor is computed by time-dependent method. The governing equations are numerically solved by MacCormack explicit scheme. The parameters of boundary points are calculated with physical boundary conditions and characteristic equations on the reference plane.

本文用时间相关法计算了固体火箭发动机燃烧室&喷管亚跨声速流场数值解，控制方程用MacCormack二步显格式：边界点参数用物理边界条件和参考平面上的特征方程计算。