Experimental Investigation of Separation and Separation Control on a Laminar Airfoil

Mack, Steffen; Brehm, Christoph; Heine, Benjamin; Kurz, Armin; Fasel, Hermann F.

doi:10.2514/6.2008-3766

Cited by 36 publications

(34 citation statements)

References 12 publications

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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%

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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Section: A C C E P T E D Mmentioning

confidence: 63%

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

Zhang

Samtaney

2016

Computers & Fluids

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“…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%

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Control of Boundary-Layer Separation for Lifting Surfaces

Balzer

Groß

Fasel

2009

2009 DoD High Performance Computing Modernization Program Users Group Conference

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The lack of understanding of most of the relevant physical mechanisms when applying flow control limits the prospects of successfully transitioning flow-control technologies into real flight vehicles. Successful control of boundary-layer separation for lifting surfaces promises major performance gains especially when large laminar runs are desired in order to minimize the skin-friction drag.We systematically explore the fundamental mechanisms of the interaction of separation and transition that are relevant for effective and efficient flow control applications.Toward this end, we are employing computational fluid dynamics (CFD) for investigating active flow control for a NACA 64 3 -618 airfoil at a chord Reynolds number Re C =64,200 and various angles-of-attack. CFD results are compared to wind/water tunnel experiments carried out at the University of Arizona. For simulations of the entire wing section we are using a high-order-accurate finite volume code based on the compressible NavierStokes equations. For very highly resolved DNS which focus exclusively on the separated region on the suction side of the wing, we are employing a higher-orderaccurate compact finite difference code based on the incompressible Navier-Stokes equations in vorticityvelocity formulation. These simulations are set up to fully resolve the flow field and enable us to reveal some of the intricate physical mechanisms associated with unsteady separation and transition, flow instabilities, and active flow control.

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“…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%

Effects of Boundary Layer Control Method on Hydrodynamic Characteristics and Tip Vortex Creation of a Hydrofoil

Ghadimi

Tanha

Kourabbasloo

et al. 2017

Polish Maritime Research

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There is currently a significant focus on using boundary layer control (BLC) approach for controlling the flow around bodies, especially the foil sections. In marine engineering this is done with the hope of increasing the lift -to -drag ratio and efficiency of the hydrofoils. In this paper, effects of the method on hydrodynamic characteristics and tip vortex formation of a hydrofoil are studied. Steady water injection at the tip of the hydrofoil is simulated in different conditions by using ANSYS-CFX commercial software. Validity of the proposed simulations is verified by comparing the obtained results against available experimental data. Effects of the injection on the lift, drag, and lift -to -dragratio are studied and the ranges within which the injection has the most positive or negative effects, are determined. Furthermore, flow pattern and pressure variation are studied upon the water injection to determine the most positive and negative case and to ascertain the main reasons triggering these phenomena.

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Experimental Investigation of Separation and Separation Control on a Laminar Airfoil

Cited by 36 publications

References 12 publications

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

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

Control of Boundary-Layer Separation for Lifting Surfaces

Effects of Boundary Layer Control Method on Hydrodynamic Characteristics and Tip Vortex Creation of a Hydrofoil

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