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首页> 外文会议>4th European Symposium on Aerothermodynamics for Space Vehicles, Oct 15-18, 2001, Capua, Italy >NUMERICAL INVESTIGATION OF TRANSIENT NOZZLE FLOW
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NUMERICAL INVESTIGATION OF TRANSIENT NOZZLE FLOW

机译：瞬态喷嘴流动的数值研究

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摘要

The starting process of two-dimensional and axisym-metric nozzle flows has been investigated numerically. Special attention has been paid to the early phase of the starting process and to the appearance of a strong secondary shock wave. For both cases, shock intensities and velocities are obtained and discussed. The flow evolution in the axisymmetric case is proved to be more complex and the transient starting process is slower than in the plane case. Finally, the effects of changing some parameters on the transient flow are addressed. It is shown that a faster start-up can be induced either by decreasing the nozzle angle or increasing the Mach number of the incident shock wave.
机译：对二维和轴对称喷嘴流的启动过程进行了数值研究。已经特别注意了启动过程的早期阶段以及强烈的二次冲击波的出现。对于这两种情况，都获得并讨论了冲击强度和速度。与轴对称情况相比，轴对称情况下的流动演化更为复杂，瞬态启动过程较慢。最后，解决了更改某些参数对瞬态流量的影响。结果表明，可以通过减小喷嘴角度或增加入射冲击波的马赫数来加快启动速度。

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