Numerical investigation on operation characteristic of ramjet projectile
Aircraft Engineering and Aerospace Technology
Article publication date: 15 July 2019
Issue publication date: 15 August 2019
The purpose of this paper is to study the operation performance of the high-speed ramjet kinetic energy projectile using solid fuel ramjet as power plant that is a new short-range and small caliber projectile.
The numerical investigation on combustion characteristic of polyethylene in high-speed ramjet kinetic energy projectile is carried out in this paper. The flow characteristics’ differences are analyzed when ramjet works or do not work, and both the combustion characteristics and propulsive performance are analyzed when ramjet works.
The results show that with the increase of the abscissa x, the flame front is close to solid fuel surface at first and then keeps away from solid fuel surface. With the increase of the abscissa x, the temperature of solid fuel surface and regression rate of solid fuel continues to increase before re-attachment point and then decreases, which a maximum locate at the re-attachment point. Both the average temperature and the regression rate on the surface of the solid fuel tend to rise as the increase of inflow Mach number. As the inflow of Mach number increases, the mass flow rate of gaseous fuel increases.
The research results can provide useful database for the subsequent research on high-speed ramjet kinetic energy projectile.
This paper studies the operation characteristics of the ramjet projectile, especially the effect of the change of the flight velocity on the performance of high-speed ramjet projectile.
This work has been financially supported by the National Natural Science Foundation (Grant No.11602109), the Jiangsu Province Natural Science Foundation of China (No. BK20160836), and the Fundamental Research Funds for the Central Universities (No. 309171B8807).
Zhuo, C.-F., Wang, M.-X., Yao, W.-J. and Xu, W.-k. (2019), "Numerical investigation on operation characteristic of ramjet projectile", Aircraft Engineering and Aerospace Technology, Vol. 91 No. 7, pp. 967-976. https://doi.org/10.1108/AEAT-03-2017-0072
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