Numerical Simulations of Effects of Micro Vortex Generators Using Immersed-Boundary Methods

Ghosh, Santanu; Choi, Jung Il; Edwards, Jack R.

doi:10.2514/1.40049

Cited by 103 publications

(39 citation statements)

References 17 publications

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“…The aforementioned larger magnitude in the neck region of MR4 is represented by the mismatch of the boundary layer profiles, indicating that this part does not follow a scaling with the ramp dimensions. The streamwise velocity profile in the center plane has also been inspected in the previous LDA study of Babinsky et al [8] and RANS study of Ghosh et al [12]. Both studies were carried out at Ma=2.…”

Section: Fig 5 Contours Of Streamwise Velocity Of Mr3 (Top) and Mr4mentioning

confidence: 99%

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Decay of the supersonic turbulent wakes from micro-ramps

et al. 2014

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This is the accepted version of the paper.This version of the publication may differ from the final published version. The wakes resulting from micro-ramps immersed in a supersonic turbulent boundary layer at Ma=2.0 are investigated by means of particle image velocimetry (PIV). Two micro-ramps are investigated with height of 60% and 80% of the undisturbed boundary layer, respectively. The measurement domain is Permanent repository link

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Section: Fig 5 Contours Of Streamwise Velocity Of Mr3 (Top) and Mr4mentioning

confidence: 99%

“…A Reynolds-averaged Navier-Stokes (RANS) simulation with immersed-boundary treatment was performed by Ghosh et al [12] (Ma=2.5, h/δ=0.46, 0.92) and the velocity profiles were compared with experiment data [8]. An acceptable agreement was only achieved for the larger micro-ramp (h/δ=0.92).…”

Section: Introductionmentioning

confidence: 99%

Decay of the supersonic turbulent wakes from micro-ramps

et al. 2014

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“…It is considered to be a hopeful substitution for bleeding control. In contrast to the conventional counterpart, the microramp vortex generator has the smaller size (approximately the height 20-40% of the boundary layer), longer streamwise distance for the vortices to remain in the boundary layer, and therefore better efficiency of the momentum exchange 9,10 . In Ref.…”

mentioning

confidence: 99%

LES Study on Mechanism of Vortex Rings behind Supersonic MVG with Turbulent Inflow

Yan

Chen

Wang

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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In this study, we investigate the interaction between vortex rings behind MVG and the oblique shocks in the MVG controlled ramp flow at M=2.5 and Re θ =5760. Implicit large eddy simulation (ILES) method is used by solving the unfiltered form of the Navier-Stokes equations with the 5th order Bandwidth-optimized WENO scheme. The fully developed inflow is given by a series of turbulent profiles obtained from previous DNS simulation. It shows that the ring structure does not break down and keeps its topology after penetrating the strong shock wave and the oblique shocks is influenced a lot by the induced flow field from rings. The bump of the 3D shock wave surface is discovered and its mechanism is explained. Nomenclature

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“…In contrast to the conventional counterpart, MVG has the smaller size (approximately the height 20-40% of the boundary layer), longer streamwise distance for the vortices to remain in the boundary layer, and therefore better efficiency of the M momentum exchange [1] [2]. In Lin's review [3] on the low-profile vortex generator, it was mentioned that MVG could alleviate the flow distortion in compact ducts to some extent and control boundary layer separation due to the adverse pressure gradients.…”

Section: Introductionmentioning

confidence: 99%

LES Study on Mechanism of Reduction of Shock Induced Flow Separation by MVG

Yang

Yan

Liu

2015

53rd AIAA Aerospace Sciences Meeting

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Shock-boundary layer interaction (SBLI) is a kind of problem which is frequently met in supersonic engine inlet flow and external flow. A detail study on mechanism of reduction of shock induced flow separation by MVG is carried out by high order implicit large eddy simulation (LES). To generate the fully developed turbulent flow, a series of turbulent profiles are given by previous DNS simulation results. The mechanism of reduction of shock induced flow separation was originally considered as a result of plump velocity profile caused by turbulent kinetic energy. It was acclaimed that turbulent flow has so stronger kinetic energy that the velocity profile is changed to be plump, which lead to reduction of shock induced flow separation. However, according to our detail study in this paper, the shock wave breaks down when ring-like vortices generated by MVG are passing through it, while the vortex structure never breaks down and is even little influenced. Therefore, the flow separation induced by shock is reduced by break-down of shock wave, not plump velocity profile. More details of the investigation on the mechanism are reported in this paper.

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Numerical Simulations of Effects of Micro Vortex Generators Using Immersed-Boundary Methods

Cited by 103 publications

References 17 publications

Decay of the supersonic turbulent wakes from micro-ramps

Decay of the supersonic turbulent wakes from micro-ramps

LES Study on Mechanism of Vortex Rings behind Supersonic MVG with Turbulent Inflow

LES Study on Mechanism of Reduction of Shock Induced Flow Separation by MVG

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