本文介绍了超音速引射喷管的流场和性能的理论计算方法。
This paper presents an analytical method for calculating the flow field and performance of supersonic ejector nozzle.
结果表明：（1）水蒸汽凝结主要发生在引射喷管和喷管出口膨胀区中。
The results show that(1) Vapour condensation occurs in ejector nozzles as well as at the regions just downstream the nozzle exit.
重点对喉部引射主喷管和燃料副喷管的不同结构、滞止参数进行探讨。
The discussing emphases are structural and stagnation parameters of ejecting nozzles and secondary fuel nozzles.
在文中所研究的引射燃烧室结构条件下，存在一个最佳二次喷管出口面积，它能使引射火箭的推力达到最大。
There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响，找到了逐步提高推力的措施。
The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually.
波瓣喷管引射器具有高效的引射掺混特性。
The ejector with a lobed nozzle is of high efficiency in pumping and mixing.
针对这种结构，本文针对不同的突片和混合管结构参数以及冷热状态下，突片状圆形喷管的引射掺混特性进行了实验研究和数值模拟计算。
To make an inquiry into the internal and external mixing aerodynamics, research was made on this kind of mixer-ejector system by a series of experiments and computations.
在双涵道的混合排气系统中，内涵出口处加装突片，外涵采用引射的方式，这是一种有别于波瓣喷管的新型掺混结构。
Tabs were used in the two-flow exhaust mixer-ejector, which compose the mixing pumping system. It is a new kind of mixer-ejector, which is different from the lobed mixer-ejector.
在双涵道的混合排气系统中，内涵出口处加装突片，外涵采用引射的方式，这是一种有别于波瓣喷管的新型掺混结构。
Tabs were used in the two-flow exhaust mixer-ejector, which compose the mixing pumping system. It is a new kind of mixer-ejector, which is different from the lobed mixer-ejector.
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