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Internal flowpath for hypersonic ramjet based on subsonic combustion
Received date: 2014-08-24
Revised date: 2014-10-20
Online published: 2014-10-21
Supported by
Science and Technology on Scramjet Laboratory Open Fund (20120103006)
To explore the performance of subsonic combustion ramjet working at hypersonic incoming flow conditions, the matching of internal flowpath of a ramjet based on dump combustion chamber is studied. The performance of the engine is obtained by means of integrated performance computation and fluid dynamics simulation. The results indicate that the designed subsonic combustion ramjet has good performance at hypersonic incoming flow conditions and works well. At the booster-to-ramjet transition point with Mach number Ma=3.5, altitude H=12 km, the thrust coefficient has its maximum value of 0.649 and the specific impulse is 13 801.2 N·s/kg. At the cruising condition with Mach number Ma=5.0, altitude H=21 km, excess air coefficient α=1.8, its specific impulse has its maximum value of 12 574.0 N·s/kg, and the thrust coefficient is 0.370. This study shows that the hypersonic ramjet with subsonic combustion for the maximum incoming Mach number between 5 and 6 is feasible.
DUAN Xihuai , ZHENG Riheng , LI Lihan . Internal flowpath for hypersonic ramjet based on subsonic combustion[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(1) : 232 -244 . DOI: 10.7527/S1000-6893.2014.0236
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