Transonic nozzle flow of dense gases
Transonic nozzle flow of dense gases
复制标题
稠密气体的跨音速喷嘴流
DOI：
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发表时间：
1993
影响因子：
3.7
通讯作者：
A. Kluwick
中科院分区：
文献类型：
--
作者：
A. Kluwick
本文研究了细长喷管喉部稠密气体的流动特性。本文从Navier-Stokes方程出发，辅以比热较大气体的实际状态方程，导出了一种新形式的粘性跨音速小扰动方程。该方程的无粘极限的评估表明，三个音速点，而不是一个单一的音速点，可能会出现在等熵膨胀的这种介质，在理想气体的情况下。因此，一般来说，用常规的收敛-扩张喷管不能实现从亚音速到超音速的无激波过渡。导致无激波流场的喷管必须有一个不寻常的形状，由两个喉道和一个中间的反喉道组成。其他新的结果包括弱激波的内部热粘性结构的计算和称为即将发生的激波分裂的现象。最后，这些结果的相关性的外部跨音速流的描述进行了简要的讨论。
The paper deals with the flow properties of dense gases in the throat area of slender nozzles. Starting from the Navier–Stokes equations supplemented with realistic equations of state for gases which have relatively large specific heats a novel form of the viscous transonic small-perturbation equation is derived. Evaluation of the inviscid limit of this equation shows that three sonic points rather than a single sonic point may occur during isentropic expansion of such media, in contrast to the case of perfect gases. As a consequence, a shock-free transition from subsonic to supersonic speeds cannot, in general, be achieved by means of a conventional converging–diverging nozzle. Nozzles leading to shock-free flow fields must have an unusual shape consisting of two throats and an intervening antithroat. Additional new results include the computation of the internal thermoviscous structure of weak shock waves and a phenomenon referred to as impending shock splitting. Finally, the relevance of these results to the description of external transonic flows is discussed briefly.