Numerical Study of the Flow Over a Circular Cylinder in the Near Wake at Reynolds Number 3900

Shim, Young-Min; Sharma, Rajnish N.; Richards, P.J.

doi:10.2514/6.2009-4160

Cited by 8 publications

(9 citation statements)

References 15 publications

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“…Comparing the current approach with URANS for the cylinder flow problems, it is not possible for URANS to faithfully reproduce the instabilities of the shear layers due to the deficient transition-modeling of most RANS models. 47,48,52 This statement is supported 6 that the current 2D result agrees better with the experimental result than the 2D RANS result from Shim et al 52 In fact, for Re > 1000, secondary vortices are developed together with a trail of small eddies that merge with the larger ones in the shear layers, 48 which can be observed in a time averaged sense in Figure 21. Compared with the time averaged streamlines from Re = 185 in Figure 18, the wake of Re = 3900 in Figure 21 has two recirculation centers instead a single one and is much shorter in length.…”

Section: 33supporting

confidence: 79%

“…Nevertheless, the goal of testing the flow over a cylinder at a higher Reynolds number is to estimate the robustness and the accuracy of the averaging solver in the sense that a steady state solution can be delivered despite high unsteadiness and that the averaging solver's solution matches the direct average of the instantaneous solver. Comparing the 2D URANS and 3D URANS results from Shim et al, 52 it can be confirmed that a 3D simulation delivers a much more realistic result. Nevertheless, Shim et al state that 3D URANS still cannot capture all flow features.…”

Section: 33mentioning

confidence: 70%

“…The time mean drag coefficient C D , the r.m.s value of the lift coefficient C L r.m.s are reported in Table 6. These values are compared with the values reported in Shim et al 52 for 2D and 3D cases. With Re = 3900, the drag and lift forces behave regularly as soon as the vortex shedding is established.…”

Section: 33mentioning

confidence: 74%

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A time averaged steady state method for the Navier–Stokes equations

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Rossi

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This work derives an incompressible variational multiscales time-averagedNavier-Stokes (NS) formulation that aims at obtaining accurate steady state solutions. Rather than using the standard time instantaneous velocity and pressure, the new formulation devises a time averaging procedure based on rewriting and solving the NS equations in terms of the newly defined time-averaged velocity and pressure. Hence, the method could be understood as a convenient change of variable so that the problem is rewritten directly in terms of the steady state quantities. The important advantage of such a point of view is that it can in principle be applied to any other formulation. Such time averaging procedure is complemented by two time step modification strategies in order to accelerate the convergence to the steady state. The guidelines of an integrated framework are presented in the article, starting with the description of the proposed numerical technique applied to general incompressible flows. The explanation is enhanced with a one-dimensional (1D) nonlinear oscillator example. Several results are presented concerning analytical benchmarks, simulation of flows in laminar, transitional and turbulent regimes with and without an inherently steady solution. K E Y W O R D Scomputational fluid dynamics, finite element method, Navier-Stokes, steady state, time-averaged, variational multiscale method This project was conducted in cooperation with International Centre for Numerical Methods in Engineering (CIMNE).This is an open access article under the terms of the Creative Commons Attribution-NonCommercial-NoDerivs License, which permits use and distribution in any medium, provided the original work is properly cited, the use is non-commercial and no modifications or adaptations are made.

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Section: 33supporting

confidence: 79%

Section: 33mentioning

confidence: 70%

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A time averaged steady state method for the Navier–Stokes equations

Zhao

Zorrilla

Rossi

et al. 2021

Numerical Methods in Fluids

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“…This case has been studied computationally using a wide variety of solvers. [11][12][13][14][15] Research conducted on this problem in the past showed that the difficulty arose due to the transitional nature of the flow at such low Reynolds number and the flow features emerging were a three-dimensional To investigate the spatial schemes present in the OVERFLOW solver, the following three schemes were selected: the third-order HLLC inviscid flux scheme, fifth-order WENO scheme, and fifth-order WENOM scheme. The spatial schemes were used in conjunction with an implicit unfactored Successive Symmetric Over Relaxation (SSOR) algorithm.…”

Section: B Previous Validationmentioning

confidence: 99%

Simulation of Various Turret Configurations at Subsonic and Transonic Flight Conditions Using OVERFLOW

Jelic¹,

Sherer

Greendyke³

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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In this work, the flow fields associated with two canonical turret geometries, a fully exposed hemisphere on a flat plate and a 50% submerged hemisphere on a flat plate, were simulated using the OVERFLOW 2 flow solver. Both turret geometries utilize a flat-window aperture with an aperture ratio (ratio of the aperture diameter to the turret diameter) of 0.295 and an elevation angle of 57 • . The forward field of regard was the particular focus in this study, and both symmetric (azimuth angle of 0 • ) and asymmetric (azimuth of 45 • ) window orientations were examined. Two flight conditions were also studied; a subsonic case with M = 0.45 and ReD = 6.30 × 10 6 and a transonic case with M = 0.85 and ReD = 9.53 × 10 6 . The flow field was simulated using the Delayed Detached Eddy Simulation capability of OVERFLOW in conjunction with the spatially fifth-order Weighted Essentially Non-Oscillatory (WENO) scheme to capture the off-body vortical structures The incoming boundary layer was set a the same height for both geometries, which corresponded to a quarter of the height of the fully exposed hemisphere and half of the height of the submerged turret. The impact of the turret aerodynamics on the performance of the turrets for directed energy applications is inferred through consideration of the flow features, density and pressure fluctuations, and forces on the turrets.

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“…To do the computational simulation first order SAS-SST turbulent model has been used on a 2-D cylinder near different wake regions and found that shape of mean velocity is related to fluctuation in velocities [7].…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of vortex induced vibrations on a circular cylinder at different Reynold’s number

Yadav¹,

Kulshreshtha²,

Singh³

2019

Vib. proced.

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This research investigates the effect of vortex induced vibrations on flow past a circular cylinder for two-dimensional unsteady incompressible flow at different Reynold's number. The pressure bases steady solver is used for computation along with standard k-ε turbulence model. The change in the lift and drag coefficient with respect to increase in Reynolds number is studied and contours of vorticity are plotted. The pressure distribution on the fixed cylinder for different Reynolds number is also presented. It is found that drag coefficient reduces with the increasing Re and lift coefficient increases up to Reynold's number 104. Moreover, the pressure difference on the fixed cylinder increases with the increasing Reynold's number.

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Numerical Study of the Flow Over a Circular Cylinder in the Near Wake at Reynolds Number 3900

Cited by 8 publications

References 15 publications

A time averaged steady state method for the Navier–Stokes equations

A time averaged steady state method for the Navier–Stokes equations

Simulation of Various Turret Configurations at Subsonic and Transonic Flight Conditions Using OVERFLOW

Numerical simulation of vortex induced vibrations on a circular cylinder at different Reynold’s number

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