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Journal of Projectiles, Rockets, Missiles and Guidance >

2019 , Vol. 39 >Issue 4: 109 - 113

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2019.04.026

Numerical Investigation on Flow Structure Characteristics of a Supersonic Split Line Nozzle

  • TONG Yue ,
  • ZHENG Qing ,
  • ZOU Jie ,
  • LI Xiuming ,
  • CHEN Zhenyang
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  • Shanghai Space Propulsion Technology Research Institute, Shanghai 201109, China

Received date: 2018-08-29

  Online published: 2025-05-19

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Abstract

A supersonic split line nozzle was numerically studied to estimate its aerodynamic advantages and obtain its flow structure and performance characteristics. Results indicate that, when the nozzle swing, the amplification factor can be greater than 1. With the increase of the swing angle, the axial thrust coefficient and amplification factor of the supersonic split line nozzle decrease obviously. When the swing angle is 7 degree, the axial thrust coefficient and amplification factor are 0.955 and 1.19, respectively. Moreover, as the distance of the split line gap increases, the high pressure zone, caused by the oblique shock, appear to drop considerably, and leading the amplification factor to decrease.

Key words： supersonic split line nozzle; swing angle; gap of split line; axial thrust coefficient; amplification factor

Cite this article

TONG Yue , ZHENG Qing , ZOU Jie , LI Xiuming , CHEN Zhenyang . Numerical Investigation on Flow Structure Characteristics of a Supersonic Split Line Nozzle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2019 , 39(4) : 109 -113 . DOI: 10.15892/j.cnki.djzdxb.2019.04.026

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