The mathematical model of turbofan engine transient process with thrust vectoring nozzle was established.
建立带矢量喷管的涡扇发动机动态数学模型。
Internal performance of unsteady flow of counterflow thrust vectoring nozzle has researched base on numerical simulation.
基于数值模拟方法，研究了逆流矢量喷管非定常内流性能。
Lastly, the results of unsteady flow point out, counterflow thrust vectoring nozzle is a efficiency fluidic vectoring nozzle.
最后，非定常流的结果进一步表明，逆流喷管是一种较高效率的射流式矢量喷管。
As thrust vectoring nozzle is the feature of advanced fighters, the difficulties in implementing thrust vectoring are summarized.
矢量喷管是先进战斗机的特征，本文讨论了实现推力矢量存在的技术难点。
The investigation shows that the separation shock wave gives an important effect on internal performance of axisymmetric vectoring nozzle.
研究结果表明，喷管内的分离激波是影响轴对称矢量喷管性能的重要因素。
A new propulsion concept of 2 D C D vectoring nozzle was proposed, which had a convergent duct shaped by spheric surface and a divergent one with rectangular transverse section.
提出了一种二元收扩矢量喷管的概念，用热射流实验台对二元矢量喷管进行了过膨胀状态下的喷管模型热态实验。
The thrust characteristics of axis symmetry nozzle were mainly measured in test. For the nozzle having a vectoring angle, the deflection efficiency was measured too.
对于轴对称喷管模型主要进行了喷管的推力特性测量，对于实施矢量偏转后的喷管模型除了给出了喷管推力特性外，还给出了喷管的偏转效率。
The vectoring Angle increases with the decreasing of the nozzle pressure ratio.
减小喷管落压比可以提高矢量偏转角度。
The vectoring Angle increases with the decreasing of the nozzle pressure ratio.
减小喷管落压比可以提高矢量偏转角度。
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