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Experimental study of near wake of micro vortex generators in supersonic flow
40th Fluid Dynamics Conference and Exhibit, 2010Detailed schlieren and laser lightsheet visualizations of the near wake of micro vortex generator (MVG) revealed large structures that were different from those of the undisturbed turbulent boundary layer. These structures were attributed to the rapid breakdown of the primary trailing vortex pair.
Frank Lu, Adam Pierce, Yusi Shih
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Separation control on high-lift airfoils via micro-vortex generators
Journal of Aircraft, 1994An experimental investigation has been conducted to evaluate boundary-layer separation control on a twodimensional single-flap, three-element, high-lift system at near-flight Reynolds numbers with small surfacemounted vortex generators. The wind-tunnel testing was carried out in the NASA Langley Low-Turbulence Pressure Tunnel as part of a cooperative ...
John C. Lin +3 more
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2021
In 2016, a new criterion called Omega vortex identification was proposed by Liu et al., which has many advantages according to several studies. However, all the existing vortex identification methods are just a scalar and they are contaminated by shear.
Xuan My Trieu, Yonghua Yan, Chaoqun Liu
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In 2016, a new criterion called Omega vortex identification was proposed by Liu et al., which has many advantages according to several studies. However, all the existing vortex identification methods are just a scalar and they are contaminated by shear.
Xuan My Trieu, Yonghua Yan, Chaoqun Liu
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Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators
40th Fluid Dynamics Conference and Exhibit, 2010Detailed experimental and numerical visualizations of the flow past a micro vortex generator (MVG) in the form of a ramp with swept sides in a Mach 2.5 flow revealed a complex near-field topology. The incoming flow separated over the leading edge of the MVG despite the ramp angle being below the threshold for incipient separation.
Frank Lu +4 more
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Numerical Simulations of Effects of Micro Vortex Generators Using Immersed-Boundary Methods
AIAA Journal, 2010This work presents an immersed-boundary technique for compressible, turbulent flows and applies the technique to simulate the effects of micro vortex generators in controlling oblique-shock/turbulent boundary-layer interactions. The Reynolds-averaged Navier-Stokes equations, closed using the Menter k-ω turbulence model, are solved in conjunction with ...
Santanu Ghosh +2 more
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Aerodynamic characteristics of a wing-in-ground effect with micro-vortex generators
Physics of FluidsMicro-vortex generators (MVGs) are simple passive flow control devices mounted on the base surfaces to mitigate the boundary layer flow separation. The effect of the MVGs installed on the aircraft lifting surfaces, i.e., wing, operating close to the ground (ground effect), is not well understood.
Abhishek Khare, Shashank Khurana
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Experimental studies on micro-vortex generators in hypersonic flow
2012Shock/boundary layer interaction (SBLI) is an undesirable phenomenon occurring in highspeed propulsion systems. The conventional method to manipulate and control SBLI is using a bleed system that removes a certain amount of mass of the inlet flow to control boundary layer separation.
Saad, M. R., Che Idris, A., Kontis, K.
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Effect of Micro Vortex Generator Width on Vortex Characteristics
AIAA AVIATION 2022 Forum, 2022Abhishek Khare, Shashank Khurana
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EFFECT OF MICRO-VORTEX GENERATOR GEOMETRY ON SEPARATION CHARACTERISTICS OF SUPERSONIC INLET
Ballistics 2025Shock boundary layer interaction (SBLI) for supersonic inlet can cause flow separation which can lead to increased drag, unstart conditions resulting in reduction in performance and efficiency. One of the important techniques of SBLI mitigation is use of micro-vortex generator (MVG) located upstream of the shock impingement in order to control the flow
Rahul Chopde +2 more
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Application of Micro-Vortex Generators for Turbulent Flow Separation Control
1999Flow separation on multi-element high-lift airfoils can be a complicated function of geometry and flight conditions, and can not be predicted reliably at this time. Previous reports have shown that certain high-lift configurations exhibit boundary-layer separation on the flap at low angles of attack, while fully attached flap flow occurs near ...
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