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.
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