Flow turbulization in a pseudo-shock forming in an axisymmetric duct with a frontal inlet

Gounko, Yu. P.; Mazhul, I. I.

doi:10.1134/s0869864318030034

Cited by 5 publications

(1 citation statement)

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“…To overcome this problem a limiter is set to the eddy-viscosity formulation with the resulting advantage of k-ω SST models are their ability to accurately predict the onset and the amount of flow separation under adverse pressure gradients Menter (1994). Gounko and Mazhul (2018) simulated the flow with a pseudo shock in an axisymmetric expanding duct with a frontal in-let at M=6.0 using k-ω-SST model. He determined the end location of the pseudo shock in a cylindrical divergent duct will be the location at which the turbulent viscosity (µt ) is maximum.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Shock Train Characteristics in Divergent Channels

Ram¹,

Kim²,

Kim³

2020

JAFM

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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.

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Section: Introductionmentioning

confidence: 99%