4th Flow Control Conference 2008
DOI: 10.2514/6.2008-3766
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Experimental Investigation of Separation and Separation Control on a Laminar Airfoil

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Cited by 36 publications
(34 citation statements)
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“…The inaccurate prediction of the leading edge separation line using a small aspect ratio has also been 505 observed by Gross & Fasel [1]. They found a spanwise straight separation line in their DNS study using AR=0.2, while the comparative experiment with AR=4.0 shows a curved separation line [69]. Although in experiments the separation is affected by various noise sources and due to the confinement by the end plates, the results of the present study confirms the inaccuracy of leading edge separation arising from an inadequacy 510 of the spanwise domain size in numerical simulations.…”
Section: A C C E P T E D Mmentioning
confidence: 63%
“…The inaccurate prediction of the leading edge separation line using a small aspect ratio has also been 505 observed by Gross & Fasel [1]. They found a spanwise straight separation line in their DNS study using AR=0.2, while the comparative experiment with AR=4.0 shows a curved separation line [69]. Although in experiments the separation is affected by various noise sources and due to the confinement by the end plates, the results of the present study confirms the inaccuracy of leading edge separation arising from an inadequacy 510 of the spanwise domain size in numerical simulations.…”
Section: A C C E P T E D Mmentioning
confidence: 63%
“…Our earlier experimental and numerical campaign [2,3] indicated that a considerable improvement of aerodynamic performance using active flow control could be expected for α=8.64° and Re C =64,200. For this particular case, using our compressible finite-volume code, we investigated active flow control by pulsed vortex generator jets (VGJs) and a plasma actuator.…”
Section: Dns Of Entire Airfoilmentioning
confidence: 96%
“…However, successful scaled flight research can only be guaranteed if the geometrically scaled model exhibits the same aerodynamics as the full size wing (aerodynamic scaling) [1] . For example, in both experiments [2] and numerical investigations [3] , it was found that at low angles-of-attack, the boundary layer separates in the aft section of the blade. This separation results in a considerably reduced slope (based on thin airfoil theory) of the lift curve (see Figure 2).…”
Section: Introductionmentioning
confidence: 96%
See 1 more Smart Citation
“…They observed the effects of injection frequency on the flow. Similarly, Mack et al [21] presented experimental results of flow control method for aerofoils. Later, Gompetz and Brunes [22] made an attempt to control the flow around aerofoil section of the wind turbines.…”
Section: Introductionmentioning
confidence: 99%