Numerical Study on Shock Train Characteristics in Divergent Channels

In any supersonic intake, the flow decelerates from supersonic to subsonic speed through a constant or divergent channel "isolator" by a series of bifurcated compression shock waves referred to as a shock train. It is important to understand the characteristics of the shock train which occ...

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Bibliographic Details
Published in:Journal of Applied Fluid Mechanics 2020-07, Vol.13 (4), p.1081-1092
Main Authors: Vignesh Ram, P. S., Kim, T. H., Kim, H. D.
Format: Article
Language:English
Subjects:
Bifurcations
Channels
Compression
Computational fluid dynamics
Computer simulation
Deceleration
Downstream effects
Longitudinal waves
Mach number
Mach reflection
Performance enhancement
Pressure
Pressure loss
Reflection
Reynolds averaged Navier-Stokes method
shock boundary layer interaction
pseudo shock wave
separated flows
shock reflection phenomenon
Shock waves
Subsonic speed
Supersonic aircraft
Supersonic combustion ramjet engines
Turbulence models
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Summary:In any supersonic intake, the flow decelerates from supersonic to subsonic speed through a constant or divergent channel "isolator" by a series of bifurcated compression shock waves referred to as a shock train. It is important to understand the characteristics of the shock train which occur inside the isolator to improve the performance of scramjet engines. In the present work, numerical simulations were carried out to investigate the characteristics of the shock train occurring in the divergent channels using coupled implicit Reynolds Averaged Navier-Stokes (RANS) equations along with the two-equation k-w SST turbulence model. Results show that the downstream pressure variation causes the shock train length to decrease and the shock structure phenomenon varies from Mach reflection to Regular reflection. The variation of the inlet Mach number has less influence on the shock train length and the location of the shock train is determined by the area ratio. In comparison with the constant area duct, the shock train structure phenomena varies from Mach reflection to regular reflection in the divergent channel. Also, the increase in divergent angle raises the total pressure loss.
ISSN:1735-3572
1735-3645
DOI:10.36884/jafm.13.04.30837