Three dimensional CFD investigation of shock train structure in a supersonic nozzle

Kamali, Reza; Mousavi, Seyed Mahmoud; Binesh, A. R.

doi:10.1016/j.actaastro.2015.06.024

Cited by 64 publications

(17 citation statements)

References 32 publications

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“…Such supersonic duct flows have been studied using both experimental and computational [22][23][24][25][26][27][28][29][30][31][32][33][34][35][36][37] approaches. The experimental studies have mainly used pressure measurements, laser Doppler velocimetry, and schlieren images to reconstruct the shocktrain structure.…”

Section: Introductionmentioning

confidence: 99%

“…The second kind of isolator simulations involves a normal shock train [25][26][27][28][29][30][31][32][33], which is more relevant to the dual-mode scramjet regime. Here, the initial shock bifurcation is caused by flow confinement, which requires either a numerical backpressure condition at the outlet or the inclusion of the combustor in the computation domain.…”

Section: Introductionmentioning

confidence: 99%

“…Here, the initial shock bifurcation is caused by flow confinement, which requires either a numerical backpressure condition at the outlet or the inclusion of the combustor in the computation domain. Reynolds-averaged Navier-Stokes simulations (RANS) [25], large-eddy simulations (LES) [27][28][29]31,34], and hybrid models [32,33] have been used. In general, LES and hybrid RANS/LES approaches have been fairly successful in capturing experimental measurements, as opposed to RANS computations [39].…”

Section: Introductionmentioning

confidence: 99%

“…In general, LES and hybrid RANS/LES approaches have been fairly successful in capturing experimental measurements, as opposed to RANS computations [39]. In particular, wall-modeled approaches or techniques that contain no special treatment for the shock-boundary-layer interaction still predict the shock-train structure reasonably well, although wall modeling was found to slightly improve predictive accuracy [31]. Such studies also demonstrated that boundary-layer modification can alter shock-train location.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of Shock-Train Response to Inflow Boundary-Layer Variations

et al. 2017

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A dataset of normal shock trains in a rectangular cross-section channel has been created from direct numerical simulations in an effort to quantify the impact of inflow confinement ratio on the shock-train structure. To this end, the inlet boundary-layer momentum thickness was varied while the bulk inflow and outflow conditions remained constant. The simulations show that the shock train is displaced upstream as the inflow confinement ratio increases. Also, an increase in boundary-layer momentum thickness results in a reduction of the normal-like portion of the lambda-shock structures in the channel core. This leads to more numerous but weaker bifurcating shocks as well as an increase of the shock-train length. When the inflow boundary-layer thickness is varied temporally, the complex shocktrain response depends on the excitation frequency. A resonant frequency is observed when different components of the shock train exhibit the highest amplification in terms of pressure jumps. Further, the domain upstream of the leading shock acts as a low-pass filter, which has the end result of limiting the axial shock-train motion. Nevertheless, even a small oscillation in boundary-layer momentum thickness of 0.45 mm (0.6% of the channel height) is seen to increase the shock-train length by two orders of magnitude (4 cm).

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of Shock-Train Response to Inflow Boundary-Layer Variations

et al. 2017

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“…Chung et al [10] used naphthalene sublimation method to investigate the flow field behavior, vortex formation and heat transfer near the nozzle end wall using CFD simulations and experiments. The work is carried on to investigate the wall pressure, flow separation, shock wave propagation and boundary layer transient flows through 3-D planar, supersonic convergent-divergent and Laval nozzle using different sub-grid models (WALE, WMLES, and Smagorinsky-Lilly) and proposed that WMLES provide best results using LES and validate it with experimental results [11][12][13]. The work was continued to predict the high pressure (70 MPa) hydrogen fluid flow behavior and its boundary layer pattern and concluded that fluid throat was generated due to viscous effects which acts as a convergent-divergent nozzle [14].…”

Section: Introduction mentioning

confidence: 99%

Design and Numerical Investigation to Predict the Flow Pattern of Non-axisymmetric Convergent Nozzle: A Component of Turboexpander

Kumar¹,

Panda²,

Biswal³

et al. 2019

JTTE

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Current work proposes a novel design methodology using curve-fitting approach for a non-axisymmetric airfoil convergent nozzle used in small-sized cryogenic turboexpander. The curves used for designing the nozzle are based on a combination of fifth and third order curve at upper and lower surface respectively. Four different turbulence model such as k-ε, SST, BSL and SSG Reynolds stress turbulence model is used to visualize and compare the fluid flow characteristics and thermal behaviors at various cross-sections. It is interesting to observe that the Mach number obtained at the outlet of the nozzle is highest and temperature drop is maximum for SSG model under similar boundary conditions. It is also observed that the designed nozzle with curve fitting approach is appropriate for impulse type turbine with a small amount of reaction. The key feature of this implementation is to obtain subsonic velocity at the nozzle exit and reduce the irreversible losses through the nozzle, which can affect the performance of a turboexpander.

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CFD analysis of Newtonian and non-Newtonian droplets impinging on heated hydrophilic and hydrophobic surfaces

2016

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Three dimensional CFD investigation of shock train structure in a supersonic nozzle

Cited by 64 publications

References 32 publications

Numerical Investigation of Shock-Train Response to Inflow Boundary-Layer Variations

Numerical Investigation of Shock-Train Response to Inflow Boundary-Layer Variations

Design and Numerical Investigation to Predict the Flow Pattern of Non-axisymmetric Convergent Nozzle: A Component of Turboexpander

CFD analysis of Newtonian and non-Newtonian droplets impinging on heated hydrophilic and hydrophobic surfaces

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