An Experimental Study of the Laminar Flow Separation on a Low-Reynolds-Number Airfoil

Hu, Hui; Yang, Zifeng

doi:10.1115/1.2907416

Cited by 100 publications

(56 citation statements)

References 20 publications

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“…Meanwhile, n   is the normal derivative on each cell face which is determined through an approach outlined in reference [27]. According to this reference, normal derivative for the unstructured mesh cell (Figure 1) is defined as follows: In Equation 15, O1 and O2 are the centers of two adjacent mesh cells, d1 is the normal distance from face AB to point O1, d2 is the normal distance from face AB to point O2,  is the angle between the line O1O2 and the normal line to the face AB, s  is the distance from A to B, while Of is the center of the face.…”

Section: Methodsmentioning

confidence: 99%

“…Ghadimi et al [14] considered the effect of splitter plates on vortex shedding of a cylinder and probed into Different experiments have also been conducted on flow around foil sections. Hu and Yang [15] conducted several experiments for investigating the flow separation near foils at low Reynolds number. Alam et al [16] performed an experimental study on the behavior of flow near NACA 0012 foil at low Reynolds numbers.…”

Section: Introductionmentioning

confidence: 99%

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Assessment of Flow Interactions Between Circular Cylinders and Naca-0018 Hydrofoils at Low Reynolds Numbers

Kermani

Ghadimi

2017

brod

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Force oscillations and flow around submerged objects at low Reynolds numbers are very important subjects in marine environments. On the other hand, NACA hydrofoils and circular sections are two of the most prevalent shapes that are applied in marine systems and due to the stated reason their hydrodynamic investigation becomes immensely important. Accordingly, in this paper, a flow solver has been developed based on finite volume method, and flow interactions between circular cylinders and NACA-0018 hydrofoils have been considered. For this purpose, different parametric studies have been conducted on the angles of attack and the distance of the foil from the cylinder at three different Reynolds numbers of 100, 200, and 300. Moreover, frequency of the lift and drag coefficients have been analyzed in different cases. As a result, suitable arrangements of the cylinders and foils are determined in the context of an energy conversion system where force fluctuation is helpful and flow around foils and cylinders where fluctuation of forces around them are harmful and vibration or noise propagation should be controlled.

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Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Assessment of Flow Interactions Between Circular Cylinders and Naca-0018 Hydrofoils at Low Reynolds Numbers

Kermani

Ghadimi

2017

brod

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“…All the numerical simulations in this study were mainly performed with the MUSIC code, a 2nd order finite volume flow solver capable of handling arbitrary meshes [16]. Although it was claimed in the PIV tests [13,15] that turbulence existed in the separation regions and played an indispensable role in the reattachment of laminar separation, the computations in the present study were done with the Navier-Stokes equation without involving any turbulence models. This could be viewed as an implicit large eddy simulation (LES) simulation, in which the numerical dissipation serves as the sub-grid model.…”

Section: A Governing Equations and Flow Solversmentioning

confidence: 99%

“…Initial conditions The experimental study on the same configurations showed no hysteresis effects [13,15], which numerically means the solution should not be dependent on the initial conditions, and thus initial condition here was just taken as freestream.…”

Section: B Numerical Uncertainty Eliminationmentioning

confidence: 99%

Computational Study of Unsteady Flows around Dragonfly and Smooth Airfoils at Low Reynolds Numbers

Gao

Wang

2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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A computational study was conducted to investigate the unsteady quasi-two-dimensional flow around a streamlined NASA low-speed GA(W)-1 airfoil and a corrugated dragonfly airfoil at the Reynolds numbers of 68,000 and 55,000. Both 2D and 3D simulations were carried out by solving the unsteady Navier-Stokes equations to predict the behavior of the unsteady flow structures around the airfoils at different angles of attack (AOAs). Extensive comparisons were made between the numerical results and wind-tunnel experimental results for the same configurations. It was found that the 2D and 3D simulations differ significantly at relatively high AOAs, and that the 3D computational results agree much better with the experimental data. It is believed that unsteady vortex-dominated flow at high angle of attack is strongly three-dimensional. As a result, the 2D simulations are not adequate in resolving the fundamental flow physics, and 3D simulations are necessary to correctly predict the flow behavior at such conditions.

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“…Transitional flows associated with separation appear for instance on compressor blades, Micro-Air Vehicles, and small household wind turbines. While laminar separation has been investigated using both experiments and numerical simulations, characterization of mushroom structures around airfoil surface at low Reynolds numbers has been mostly conducted experimentally [1,2,3,4,5].…”

Section: Introductionmentioning

confidence: 99%

URANS simulations of separated flow with stall cells over an NREL S826 airfoil

Sarlak

Nishino

Sørensen

2016

AIP Conference Proceedings

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An Experimental Study of the Laminar Flow Separation on a Low-Reynolds-Number Airfoil

Cited by 100 publications

References 20 publications

Assessment of Flow Interactions Between Circular Cylinders and Naca-0018 Hydrofoils at Low Reynolds Numbers

Assessment of Flow Interactions Between Circular Cylinders and Naca-0018 Hydrofoils at Low Reynolds Numbers

Computational Study of Unsteady Flows around Dragonfly and Smooth Airfoils at Low Reynolds Numbers

URANS simulations of separated flow with stall cells over an NREL S826 airfoil

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