Experimental determination of the main features of the viscous flow in the wake of a circular cylinder in uniform translation. Part 1. Steady flow

Coutanceau, Madeleine; Bouard, R.

doi:10.1017/s0022112077000135

Cited by 496 publications

(272 citation statements)

References 29 publications

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“…The separation length measured from the rear stagnation point of the cylinder in cylinder diameters, the separation angle which defines the point of separation from the body, and the drag coefficient in each case are also shown in Table 1.They are consistent with the experimental data [15,16] and the computational results listed in [4]. The errors of the separation length and separation angle relative to [16] are 2.35% and 0.37% respectively, and that of the drag coefficient relative to [15] is 2.42%. Moreover, all the errors of the numerical results relative to the experimental data are less than 5%, which demonstrate the reliability of the present method.…”

Section: Low Reynolds Number Flow Over Circular Cylindersupporting

confidence: 82%

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Preconditioned HLLC scheme for incompressible viscous flow simulation

Qian¹,

Lee²

2012

Advances in Fluid Mechanics IX

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A new HLLC approximate Riemann solver with preconditioning technique based on the pseudo-compressibility formulation for numerical simulation of the incompressible viscous flows has been proposed, which follows the HLLC Riemann solver (Harten, Lax and van Leer solver with contact resolution modified by Toro) for the compressible flow system. In the authors' previous work, the preconditioned Roe's Riemann solver was applied to the finite difference discretization of the inviscid flux. Although the Roe's Riemann solver is found to be an accurate and robust scheme in various numerical computations, the HLLC Riemann solver is more suitable for the pseudo-compressible NavierStokes equations, in which the inviscid flux vector is a non-homogeneous function of degree one of the flow field vector; however the Roe's solver is restricted to the homogeneous problems. Numerical investigations have been performed in order to demonstrate the efficiency and accuracy of the present procedure. The present results are found to be good agreement with the exact solutions, existing numerical results or experimental data.

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Section: Low Reynolds Number Flow Over Circular Cylindersupporting

confidence: 82%

“…The low Reynolds number incompressible flow over a circular cylinder is a benchmark problem for incompressible flows, for which many experimental and computational results can be utilized for comparison [4,15,16]. In this section, the problem is simulated by the algorithm proposed in previous sections.…”

Section: Low Reynolds Number Flow Over Circular Cylindermentioning

confidence: 99%

Preconditioned HLLC scheme for incompressible viscous flow simulation

Qian¹,

Lee²

2012

Advances in Fluid Mechanics IX

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“…For the next iteration, one makes a correction (Δf x , Δf y ) to the external force to eliminate the discrepancy between the resulting velocity and that from the interpolation procedure (33) and (34), i.e.…”

Section: The Implicit Virtual Boundary Methodsmentioning

confidence: 99%

“…For both cases of Re = 20 and Re = 40, there is a stable recirculation zone behind the cylinder that contains a pair of symmetric vortices. To examine the accuracy of the predicted wake structure, the present numerical results for the length of the recirculation zone l/D, distance from the cylinder to the centers of the vortices a/D, the gap between the centers of the vortices b/D, the separation angle θ s , and the drag coefficient C D are compared with that from the existing experimental and numerical studies [33][34][35][36] in Table 1. Good agreements among the results are seen.…”

Section: Uniform Flow Past a Stationary Cylindermentioning

confidence: 99%

Implicit Virtual Boundary Method for Moving Boundary Problems on Non-Staggered Cartesian Patch Grids

2017

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A simple numerical method is proposed in the paper for fluid flow around a moving boundary of irregular shape. The unsteady term is discretized with the implicit scheme such that large time step is allowed. All of the computations are performed on non-staggered Cartesian grid system. Fine Cartesian patch grid system covering the moving object is employed to resolve the solution around the solid body. A closed curve defined by connecting the solid grid points adjacent to the solid-liquid interface is referred to as virtual boundary. The narrow irregular strip of solid between the virtual boundary and the actual solid-fluid interface is called pseudo-fluid. The general fluid region consisting of both fluid and pseudo-fluid is a regular domain that can be efficiently solved with conventional numerical method. In this connection, external force is imposed at each fluid grid point adjacent to the solid-fluid interface to compensate for the numerical error arising from the assumption of pseudo-fluid. The solution procedure is iterated until the required external force converges. Accuracy of the new numerical method is validated through three test problems. The numerical method then is used to investigate the flow induced by the flapping wings of a tethered dragonfly in literature. The corresponding CFL numbers of the four examples are infinity, 20, 100, and 3.29.

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“…results (Berthelsen and Faltinsen 2008;Russel and Wang 2003;Linnick and Fasel 2005;Herfjord 1996;Calhoun 2002;Medjroubi 2011;Coutanceau and Bouard 1977;Tritton 1959). In order to compare the efficiency of the present method concerning other numerical methods, the average of error in other numerical results is calculated.…”

Section: Algorithm Validationmentioning

confidence: 99%

Detailed Numerical Study on the Aerodynamic Behavior of a Gurney Flapped Airfoil in the Ultra-low Reynolds Regime

Khoshlessan¹,

Karimian²

2017

J.Aerosp. Technol. Manag.

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The addition of Gurney flap changes the nature of flow around airfoil by producing asymmetric VonKarman vortex in its wake. Most of the investigations on Gurney flapped airfoils have modeled the flow using a quasisteady approach, resulting in time-averaged values with no information on the unsteady features of the flow. Among these, some investigations have shown that quasi-steady approach does a good job on predicting the aerodynamic coefficients and physics of flow. Previous studies on Gurney flap have shown that the calculated aerodynamic coefficients such as lift and drag coefficients from quasi-steady approach are in good agreement with the time averaged values of these quantities in time accurate computations. However, these investigations were conducted in regimes of medium to high Reynolds numbers where the flow is turbulent. Whether this is true for the regime of ultra-low Reynolds number is open to question. Therefore, it is deemed necessary to examine the previous investigations in the regime of ultra-low Reynolds numbers. The unsteady incompressible laminar flow over a Gurney flapped airfoil is investigated using three approaches; namely unsteady accurate, unsteady inaccurate, and quasisteady. Overall, all the simulations showed that at ultra-low Reynolds numbers quasi-steady solution does not necessarily have the same correlation with the time averaged results over the unsteady accurate solution. In addition, it was observed that results of unsteady inaccurate approach with very small time steps can be used to predict time-averaged quantities fairly accurate with less computational cost.

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Experimental determination of the main features of the viscous flow in the wake of a circular cylinder in uniform translation. Part 1. Steady flow

Cited by 496 publications

References 29 publications

Preconditioned HLLC scheme for incompressible viscous flow simulation

Preconditioned HLLC scheme for incompressible viscous flow simulation

Implicit Virtual Boundary Method for Moving Boundary Problems on Non-Staggered Cartesian Patch Grids

Detailed Numerical Study on the Aerodynamic Behavior of a Gurney Flapped Airfoil in the Ultra-low Reynolds Regime

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