Effects of End Plates and Blockage on Low-Reynolds-Number Flows Over Airfoils

Boutilier, Michael S. H.; Yarusevych, Serhiy

doi:10.2514/1.j051469

Cited by 47 publications

(22 citation statements)

References 33 publications

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“…3.4), as per the recommendation of Boutilier and Yarusevych [156]. The solid blockage ratios were within the range of 7.4% to 12.8%.…”

Section: Airfoil Modelmentioning

confidence: 72%

“…In order to minimize end effects, measurements were performed at the midspan plane of the airfoil. At this location, surface pressure distributions are approximately two-dimensional at low angles of attack [156]. In these experiments, performed at an angle of attack of 4°, the estimated solid blockage ratio is 5.9% and no solid blockage corrections were applied.…”

Section: Airfoil Modelmentioning

confidence: 99%

“…The solid blockage ratios were within the range of 7.4% to 12.8%. In this range of blockage ratios, blockage corrections [157,158] can be applied below the stall angle of attack [156], however, the corrections perform poorly in the post-stall regime and, therefore, for consistency, no blockage corrections were applied to the results of this investigation.…”

Section: Airfoil Modelmentioning

confidence: 99%

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Effects of free-stream turbulence intensity on laminar separation bubbles

Istvan

Kurelek

Yarusevych

2016

46th AIAA Fluid Dynamics Conference

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“…3.4), as per the recommendation of Boutilier and Yarusevych [156]. The solid blockage ratios were within the range of 7.4% to 12.8%.…”

Section: Airfoil Modelmentioning

confidence: 72%

Section: Airfoil Modelmentioning

confidence: 99%

Section: Airfoil Modelmentioning

confidence: 99%

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Effects of free-stream turbulence intensity on laminar separation bubbles

Istvan

Kurelek

Yarusevych

2016

46th AIAA Fluid Dynamics Conference

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“…The airfoil was installed approximately 0.15 m downstream of the test section nozzle (figure 1) between two circular end plates spaced by two chord lengths, complying with the recommendations for end-plate spacing of Boutilier & Yarusevych (2012a). The model was positioned at geometric angle of attack α = 2 • with the associated uncertainty of approximately 0.1 • .…”

Section: Experimental Set-upmentioning

confidence: 99%

Laminar separation bubble development on an airfoil emitting tonal noise

2015

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The subject of this experimental study is the feedback effects due to tonal noise emission in a laminar separation bubble (LSB) formed on the suction side of an airfoil in low Reynolds number flows. Experiments were performed on a NACA 0012 airfoil for a range of chord-based Reynolds numbers 0.65 × 10 5 Re c 4.5 × 10 5 at angle of attack α = 2 • , where laminar boundary layer separation is encountered on both sides of the airfoil. Simultaneous time-resolved, two-component particle image velocimetry (PIV) measurements, unsteady surface pressure and far-field acoustic pressure measurements were employed to characterize flow development and acoustic emissions. Amplification of disturbances in separated shear layers on both the suction and pressure sides of the airfoil leads to shear layer roll-up and shedding of vortices from separation bubbles. When the vortices do not break up upstream of the trailing edge, the passage of these structures over the trailing edge generates tonal noise. Acoustic feedback between the trailing edge noise source and the upstream separation bubble narrows the frequency band of amplified disturbances, effectively locking onto a particular frequency. Acoustic excitation further results in notable changes to the overall separation bubble characteristics. Roll-up vortices forming on the pressure side, where the bubble is located closer to the trailing edge, are shown to define the characteristic frequency of pressure fluctuations, thereby affecting the disturbance spectrum on the suction side. However, when the bubble on the pressure side is suppressed via boundary layer tripping, a weaker feedback effect is also observed on the suction side. The results give a detailed quantitative description of the observed phenomenon and provide a new outlook on the role of coherent structures in separation bubble dynamics and trailing edge noise generation.

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“…It is seen in the table that the aspect ratio of the airfoil is normally larger than 1.0, which is larger than most simulation studies. Boutilier & Yarusevych [6] investigated the effect of the end plates on flow past a NACA0018 airfoil at Re=10 5 and AoA=0-15 degrees, 65 and found that the existence of the end plates improves the mean spanwise uniformity.…”

Section: A C C E P T E D Mmentioning

confidence: 99%

Assessment of spanwise domain size effect on the transitional flow past an airfoil

Zhang

Samtaney

2016

Computers & Fluids

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Please cite this article as: Wei Zhang, Ravi Samtaney, Assessment of spanwise domain size effect on the transitional flow past an airfoil, Computers and Fluids (2015), doi: 10.1016/j.compfluid.2015 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting proof before it is published in its final form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. ACCEPTED MANUSCRIPTA C C E P T E D M A N U S C R I P T Highlights• DNS on the separated-transitional-reattached flow past the airfoil.• The effects of the spanwise domain size are analyzed from various aspects.• The spanwise domain size has significant effects on the various turbulent statistics.• Small spanwise domain size tends to underpredict the spanwise variations.• Examination through only a few quantities may lead to misleading conclusion.

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Effects of End Plates and Blockage on Low-Reynolds-Number Flows Over Airfoils

Cited by 47 publications

References 33 publications

Effects of free-stream turbulence intensity on laminar separation bubbles

Effects of free-stream turbulence intensity on laminar separation bubbles

Laminar separation bubble development on an airfoil emitting tonal noise

Assessment of spanwise domain size effect on the transitional flow past an airfoil

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