Abstract: An analytical method for computing the performance of thrust augmentation ejector at primary flow pressure ratio above choking point and some experimental results of scale ejector model are presented in this paper.The comparison between the computational results of the performance by this method and the experimental data indicate a very good agreement.

Key words: Shrouded nozzle;Performance analysis;Nozzle flow;Experiment;Jet VTOL aircraft

摘要： 本文叙述了在主流超临界压力比下,引射增力器的性能计算方法,及缩尺寸增力器模型的一些实验结果。比较结果表明:二者能较好地相符。

关键词: 引射喷管;性能分析;喷管气流;试验;喷气式垂直起落飞机