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。
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。
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。
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