Review of Micro Vortex Generators in High-Speed Flow

Lu, Frank K.; Li, Qin; Shih, Yusi; Pierce, Adam J.; Liu, Chaoqun

doi:10.2514/6.2011-31

Cited by 32 publications

(20 citation statements)

References 70 publications

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“…Micro-vortex generators (MVGs) are positioned upstream of the SWBLI, and have been shown to eliminate or reduce separation by entraining high-momentum fluid from the freestream (or outer boundary layer) by means of streamwise vortices to energize the low-momentum near-wall boundary layer flow. The low profile of the microvortex generators is thought to reduce the wave drag associated with traditional vortex generators while still providing strong enough vortices to reduce separation [7][8][9][10][11][12][13][14]. Investigations into the use of MVGs for reducing shock oscillation have also been conducted [15][16][17][18][19].…”

Section: Introductionmentioning

confidence: 96%

“…Numerous recent studies have investigated the use of sub-boundary layer vortex generators (SBVGs) in order to replace bleed as a method of reducing or eliminating shock wave/boundary layer interaction (SWBLI) separation and improving boundary layer health in supersonic inlets [7][8][9][10][11][12][13][14]. These sub-boundary layer, micro-, or low-profile vortex generators are similar to traditional vortex generators, but with heights less than the boundary layer thickness [7].…”

Section: Introductionmentioning

confidence: 98%

See 1 more Smart Citation

High-Speed Schlieren Analysis of Buzz in a Relaxed-Compression Supersonic Inlet

Herges¹,

Dutton²,

Elliott³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The buzz cycle of a supersonic axisymmetric relaxed external compression inlet has been investigated in the 8'x6' supersonic wind tunnel at NASA Glenn Research Center. This inlet entails a mechanically simple design for providing a high-recovery/low-distortion flowfield and low sonic boom signature. Inlet buzz occurred at low mass-flow ratios with various vortex-generator configurations and Mach number values, providing an abundance of buzz data. High-speed schlieren and pressure measurements were used to characterize the inlet buzz. Schlieren movies not only allowed the characterization of the buzz cycle but also permitted the shock position to be tracked in time so that the frequency of the shock motion could be evaluated. The analysis revealed a dominant low frequency oscillation at 21.0 Hz corresponding with the duration of one buzz cycle. High-frequency shock position oscillations (spike buzz) were also observed throughout portions of the inlet buzz cycle.

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Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 98%

High-Speed Schlieren Analysis of Buzz in a Relaxed-Compression Supersonic Inlet

Herges¹,

Dutton²,

Elliott³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…An excellent comprehensive review of boundary-layer flow-separation control by a passive method and their applications had been compiled by [12][13]. There are numerous other reported studies on the control of separation in turbulent boundary layers using low profile vortex generators.…”

Section: Introductionmentioning

confidence: 99%

Boundary Layer Control of an Axial Compressor Cascade Using Nonconventional Vortex Generators

Diaa

El-Dosoky

Ahmed

et al. 2015

Volume 1: Advances in Aerospace Technology

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Boundary layer control plays a decisive role in controlling the performance of axial compressor. Vortex generators are well known as passive control devices of the boundary layer. In the current study, two nonconventional types of vortex generators are used and their effects are investigated. The used vortex generators are doublet, and wishbone. Three dimensional turbulent compressible flow equations through an axial compressor cascade are numerically simulated. Comparisons between cascade with and without vortex generators are performed to predict the effect of inserting vortex generator in the overall performance of the axial compressor. Results indicate that using vortex generators leads to eliminate or delay the separation on the blade suction surface, as well as the endwall. Furthermore, the effects of the vortex generators and their geometrical parameters on the aerodynamic performance of the cascade are documented. In conclusion, while the investigated vortex generators cause a slight increase in the total pressure loss, a significant reduction in the skin friction coefficient at the bottom endwall is found. This reduction is estimated to be about 46% using doublet and 32% using wishbone.

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“…A lot of research has been carried out, throughout decades, leading to a variety of Vortex Generator's (VG) shapes, including small size sub-layer VGs. A review of the state of the art concerning low-profile vortex generators applied to flow separation control was conducted by Lin 3 and micro vortex generators in high speed is reviewed by Lu et al 4 .…”

mentioning

confidence: 99%

Comparison of vortex generators effect on shock wave induced separation

Flaszyński

2016

8th AIAA Flow Control Conference

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Application of Jet Vortex Generator and Rod Vortex Generator and its effect on the shock wave induced separation is compared. Experimental investigations have been carried out in the test section with curved wall. The flow in the curved nozzle accelerates along the lower wall creating a local supersonic zone. Upstream of the shock wave, Mach number is 1.43 and the boundary layer separation appears downstream. In the paper, the effect of both vortex generators on the separation is presented by means of: the boundary layer measurements, static pressure distribution at the wall, oil flow visualisation and schlieren pictures. Nomenclature D = diameter h = rod height L = spanwise distance JVG = jet vortex generator M = Mach number RVG = rod vortex generator Ps = static pressure P0 = total inlet pressure U' = velocity fluctuations U'noVG = velocity fluctuations for reference case VG = vortex generator X, Y, Z = cartesian coordinates 99 = boundary layer thickness 1= displacement thickness ϕ = pitch angle (jet or rod)  = skew angle (jet or rod)

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Review of Micro Vortex Generators in High-Speed Flow

Cited by 32 publications

References 70 publications

High-Speed Schlieren Analysis of Buzz in a Relaxed-Compression Supersonic Inlet

High-Speed Schlieren Analysis of Buzz in a Relaxed-Compression Supersonic Inlet

Boundary Layer Control of an Axial Compressor Cascade Using Nonconventional Vortex Generators

Comparison of vortex generators effect on shock wave induced separation

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