Journal of Projectiles, Rockets, Missiles and Guidance >
Numerical Investigation on Combustion Performance, Solid Rocket Scramjet
Received date: 2013-05-03
Online published: 2025-05-29
For increasing the performance of mixing and combustion, the scramjet was developed, which consists of axisymmetric combustor with expanding degree. The numerical simulation including simple chemical mechanism was developed to investigate the reactive flow characteristics for supersonic combustion in circular combustor solid rocket scramjet which is combined with vortex generator and cavity. It is indicated that the expanding degree of combustor can increase the combustion efficiency to a certain extent: The combustion reaction would be improved by using cavity configuration whereas the internal resistance would be great; The combustion efficiency is obviously enhanced due to the vortex generator can augment the mixing intensity of the fuel-rich gas.
Key words： scramjet; solid rocket; numerical simulation; mixing intensity
LI Xuan , MA Lifeng , ZHAO Yongtao , YANG Yuxin , DONG Xingang . Numerical Investigation on Combustion Performance, Solid Rocket Scramjet[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2014 , 34(1) : 104 -107,161 . DOI: 10.15892/j.cnki.djzdxb.2014.01.011
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