本文提出了确定气动窗口所需自由旋涡气动特性的过程，讨论了特征线方法在非对称超音速喷管设计中的应用，该喷管被用来产生自由旋涡流动。
In this article the procedures are described for determining free vortex segment properties. Characteristics method is used to design nozzle which produces free vortex segment.
指出，当超音速飞行时，在前喷管附近的弹体表面上产生一个局部高压区，由此形成一个翻转力矩。
It is demonstrated that there exists a part of high pressure on the body surface of the rocket near the fore-located nozzles, thus forming a overturning moment.
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.
实验结果表明，冲压室燃烧效率比采用音速(或超音速)单喷管时提高30%左右。
The secondary combustion efficiency with this type of nozzles was increased by about 30% than that with single sonic (or supersonic) rocket nozzles.
用小型电弧加热器对筛形喷管CO_2 - N_2超音速混合气动激光器进行了实验研究。
Experimental study on a CO_2-N_2 supersonic mixing GDL with a screen nozzle was performed on a small scale electric-ar (?) heater.
利用特征线方法数值模拟了双圆弧和抛物线两种特型喷管中的三维非对称定常等熵的超音速流场。
Numerical simulation of three-dimensional, steady, isentropic, non-symmetrical flow in rocket nozzles is completed using a bicharacteristic method.
研究了当气流偏离抛物型喷管超音速段对称轴时所引起的喷管推力偏心。
Thrust misalignment in parabolic nozzle is investigated for the situation where the gas flow is misaligned with respect to the axis of the supersonic region of the nozzle.
利用数值模拟方法对采用高超音速低温喷管（HYLTE）线性阵列DF化学激光器进行了研究。
The DF chemical laser, adopting the Hypersonic-Low Temperature(HYLTE) nozzle in linear array form, was numerically studied.
最后，本文针对两种构型的超音速尾喷管，对其流场进行了计算和分析。
In final section of this paper, the flow field of two types of supersonic nozzle for scramjet is simulated and analyzed.
建立了超音速气固两相分离装置试验系统，在室温和不同喷管进口全压下，对空心玻璃珠颗粒的分离效率进行了试验研究。
Separation efficiencies of hollow glass beads were measured under room temperature and different nozzle inlet total pressures from 482 kPa to 537 kPa.
建立了超音速气固两相分离装置试验系统，在室温和不同喷管进口全压下，对空心玻璃珠颗粒的分离效率进行了试验研究。
Separation efficiencies of hollow glass beads were measured under room temperature and different nozzle inlet total pressures from 482 kPa to 537 kPa.
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