Loads on a Harmonically Oscillating Cylinder

2007 ◽  
Author(s):  
Osama A. Marzouk ◽  
Ali H. Nayfeh
Keyword(s):  
Reynolds Number ◽  
Spectral Analysis ◽  
Abrupt Change ◽  
Phase Portraits ◽  
Near Wake ◽  
Harmonic Motion ◽  
Synchronization Region ◽  
Second Mode ◽  
Shedding Frequency ◽  
Lift And Drag

A harmonic motion of a cylinder acts as a forcing source to the near wake. Depending on the amplitude and frequency of this motion, the lift exerted on the cylinder may be synchronized or not synchronized with the frequency of the motion. Here, we numerically investigate the behavior of the wake, particularly the induced forces on the cylinder, at a low Reynolds number when the forcing frequency is varied from half to twice the shedding frequency of the wake. Within the synchronization region, an abrupt change in the wake, reflected in a discontinuity in the lift, leads to two different flow modes. In the first mode, increasing the motion frequency causes the lift to increase; whereas in the second mode, this relation is reversed. We analyzed the behavior outside the synchronization region, where the lift is not synchronized with the motion. Poincare´ sections, phase portraits, and spectral analysis were used to characterize different behaviors (e.g., period-n, quasi-periodic, and chaos) of the lift and drag. Also, we performed nonstationary analysis in which the cylinder frequency was varied with different rates and observed typical nonstationary responses in which the jumps were eliminated.

Effect of Tube Spacing on the Vortex Shedding Characteristics of Laminar Flow Past an Inline Tube Array

2008 ◽  
Author(s):  
C. Liang ◽  
X. Luo ◽  
G. Papadakis
Keyword(s):  
Reynolds Number ◽  
Vortex Shedding ◽  
Unstructured Grid ◽  
Flow Patterns ◽  
Instantaneous Flow ◽  
Flow Past ◽  
Recirculation Zones ◽  
Shedding Frequency ◽  
Drag And Lift ◽  
Lift And Drag

The effect of tube spacing on the vortex shedding characteristics and fluctuating forces in an inline tube array is examined. The array consists of 6 cylinders in tandem, the examined Reynolds number is 100 and the flow is laminar. The numerical methodology and the code employed to solve the equations in an unstructured grid are validated against available results from the literature for the flow past two cylinders in tandem. Computations are then performed for the 6 row inline bank for 8 pitch-to-diameter ratios s ranging from 2.1 to 4. The instantaneous flow patterns are visualised for different spacings and the lift and drag coefficients for all cylinders are recorded and analysed. At the smallest spacing examined (s = 2.1) there are five stagnant and symmetric recirculation zones and weak vortex shedding activity occurs behind the last cylinder only. As s increases, the symmetry of the recirculation zones breaks leading to vortex shedding. This process progressively moves upstream, so that for s = 4 there is clear shedding for every row. The shedding frequency behind each cylinder is the same and increases with tube spacing. A spacing region between 3d and 3.6d is identified, within which rms drag and lift coefficients attain maximum values. This behaviour is explained with the aid of instantaneous flow patterns.

Characteristics of Flow Past a Symmetric Airfoil at Low Reynolds Number: A Nonlinear Perspective

2012 ◽  
Author(s):  
M. Saif Ullah Khalid ◽  
Imran Akhtar
Keyword(s):  
Reynolds Number ◽  
Period Doubling ◽  
Nonlinear Behavior ◽  
Phase Portraits ◽  
Aerodynamic Forces ◽  
Flow Past ◽  
Time Histories ◽  
Lift And Drag ◽  
Naca 0012 ◽  
Even Harmonics

Flow separation in airfoils have been extensively studied to analyze the underlying physics of the phenomenon. The phenomenon being nonlinear requires tools to reveal various features involving stall, bifurcation, and transition to chaos. In this study, we perform numerical simulations of the flow past a symmetric airfoil (NACA-0012) at 1,000 Reynolds number to compute the aerodynamic forces at different angles of attack (α). The time histories and spectral analysis reveal important features of nonlinear behavior in the flow around the airfoil. We find that the steady state temporal solutions for aerodynamic forces; lift and drag, contain both odd and even harmonics which indicate the presence of quadratic as well as cubic nonlinearity in the system. These results also help to understand nonlinear behavior of the system as a function of α. Considering the angle of attack for airfoil as a control parameter, we observe that to achieve the static stall, flow becomes chaotic adopting a route through period-doubling and quasi-periodic regimes. Using phase portraits and Poincare maps between the states of the system, period-doubling is observed in this nonlinear system at α = 22° leading to chaos at α = 27°.

Proximity-induced galloping of two interfering circular cylinders

1984 ◽  
Vol 146 ◽  
pp. 417-449 ◽  
Author(s):  
A. Bokaian ◽  
F. Geoola
Keyword(s):  
Circular Cylinders ◽  
Appreciable Effect ◽  
Dynamic Tests ◽  
Near Wake ◽  
Drag Coefficients ◽  
Free Stream Turbulence ◽  
Plane Normal ◽  
Vortex Shedding Frequency ◽  
Shedding Frequency ◽  
Lift And Drag

Experiments were conducted to investigate the response of a rigid two-dimensional elastically mounted smooth circular cylinder, with oscillations restricted to a plane normal to the incident flow, as influenced by the vicinity of an identical fixed body placed inside the wake. The static lift and drag coefficients, as well as the vibration amplitude and frequency of the upstream cylinder as functions of relative position of the pair of cylinders are given. Most measurements were carried out under two conditions of free-stream turbulence. Whilst turbulence decreased the magnitude of drag coefficients, it had no appreciable effect on lift coefficients. The forces on the upstream body were found to be influenced by the proximity to the downstream one in a significant way only when the streamwise spacing is less than two diameters.In the dynamic tests, two kinds of instability, namely a vortex-resonance and galloping, were observed, with the latter only occurring when the downstream cylinder was well submerged in the near wake of the upstream one. The vortex-shedding frequency was always found to lock to oscillation frequency. Whereas the vibration characteristics remained essentially unaffected with changing turbulence intensity, the galloping amplitudes were observed to be sensitive to cylinders’ aspect ratio. A quasi-steady theory was developed to predict the galloping behaviour.

Heat transfer enhancement using second mode self-oscillating structures

2019 ◽  
Vol 30 (7) ◽  
pp. 3827-3842
Author(s):  
Samer Ali ◽  
Zein Alabidin Shami ◽  
Ali Badran ◽  
Charbel Habchi
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Nusselt Number ◽  
Laminar Flow ◽  
Flow Regime ◽  
Vortex Generator ◽  
Reynolds Numbers ◽  
Content Type ◽  
Laminar Flow Regime ◽  
Second Mode

Purpose In this paper, self-sustained second mode oscillations of flexible vortex generator (FVG) are produced to enhance the heat transfer in two-dimensional laminar flow regime. The purpose of this study is to determine the critical Reynolds number at which FVG becomes more efficient than rigid vortex generators (RVGs). Design/methodology/approach Ten cases were studied with different Reynolds numbers varying from 200 to 2,000. The Nusselt number and friction coefficients of the FVG cases are compared to those of RVG and empty channel at the same Reynolds numbers. Findings For Reynolds numbers higher than 800, the FVG oscillates in the second mode causing a significant increase in the velocity gradients generating unsteady coherent flow structures. The highest performance was obtained at the maximum Reynolds number for which the global Nusselt number is improved by 35.3 and 41.4 per cent with respect to empty channel and rigid configuration, respectively. Moreover, the thermal enhancement factor corresponding to FVG is 72 per cent higher than that of RVG. Practical implications The results obtained here can help in the design of novel multifunctional heat exchangers/reactors by using flexible tabs and inserts instead of rigid ones. Originality/value The originality of this paper is the use of second mode oscillations of FVG to enhance heat transfer in laminar flow regime.

scholarly journals Flow past a square-section cylinder with a wavy stagnation face

2001 ◽  
Vol 426 ◽  
pp. 263-295 ◽  
Author(s):  
RUPAD M. DAREKAR ◽  
SPENCER J. SHERWIN
Keyword(s):  
Reynolds Number ◽  
Cross Flow ◽  
Leading Edge ◽  
Reynolds Numbers ◽  
Physical Structure ◽  
Near Wake ◽  
Hairpin Vortices ◽  
Independent State ◽  
Flow Past ◽  
Edge Surface

Numerical investigations have been performed for the flow past square-section cylinders with a spanwise geometric deformation leading to a stagnation face with a sinusoidal waviness. The computations were performed using a spectral/hp element solver over a range of Reynolds numbers from 10 to 150.Starting from fully developed shedding past a straight cylinder at a Reynolds number of 100, a sufficiently high waviness is impulsively introduced resulting in the stabilization of the near wake to a time-independent state. It is shown that the spanwise waviness sets up a cross-flow within the growing boundary layer on the leading-edge surface thereby generating streamwise and vertical components of vorticity. These additional components of vorticity appear in regions close to the inflection points of the wavy stagnation face where the spanwise vorticity is weakened. This redistribution of vorticity leads to the breakdown of the unsteady and staggered Kármán vortex wake into a steady and symmetric near-wake structure. The steady nature of the near wake is associated with a reduction in total drag of about 16% at a Reynolds number of 100 compared with the straight, non-wavy cylinder.Further increases in the amplitude of the waviness lead to the emergence of hairpin vortices from the near-wake region. This wake topology has similarities to the wake of a sphere at low Reynolds numbers. The physical structure of the wake due to the variation of the amplitude of the waviness is identified with five distinct regimes. Furthermore, the introduction of a waviness at a wavelength close to the mode A wavelength and the primary wavelength of the straight square-section cylinder leads to the suppression of the Kármán street at a minimal waviness amplitude.

Strouhal Number for VIV Excitation of Long Slender Structures

2018 ◽  
Author(s):  
Andrew E. Potts ◽  
Douglas A. Potts ◽  
Hayden Marcollo ◽  
Kanishka Jayasinghe
Keyword(s):  
Reynolds Number ◽  
Strouhal Number ◽  
Degrees Of Freedom ◽  
Measurement Techniques ◽  
Cross Flow ◽  
Degree Of Freedom ◽  
Circular Cylinders ◽  
Two Degrees Of Freedom ◽  
Shedding Frequency ◽  
Eddy Shedding

The prediction of Vortex-Induced Vibration (VIV) of cylinders under fluid flow conditions depends upon the eddy shedding frequency, conventionally described by the Strouhal Number. The most commonly cited relationship between Strouhal Number and Reynolds Number for circular cylinders was developed by Lienhard [1], whereby the Strouhal Number exhibits a consistent narrow band of about 0.2 (conventional across the sub-critical Re range), with a pronounced hump peaking at about 0.5 within the critical flow regime. The source data underlying this relationship is re-examined, wherein it was found to be predominantly associated with eddy shedding frequency about fixed or stationary cylinders. The pronounced hump appears to be an artefact of the measurement techniques employed by various investigators to detect eddy-shedding frequency in the wake of the cylinder. A variety of contemporary test data for elastically mounted cylinders, with freedom to oscillate under one degree of freedom (i.e. cross flow) and two degrees of freedom (i.e. cross flow and in-line) were evaluated and compared against the conventional Strouhal Number relationship. It is well established for VIV that the eddy shedding frequency will synchronise with the near resonant motions of a dynamically oscillating cylinder, such that the resultant bandwidth of lock-in exhibits a wider range of effective Strouhal Numbers than that reflected in the narrow-banded relationship about a mean of 0.2. However, whilst cylinders oscillating under one degree of freedom exhibit a mean Strouhal Number of 0.2 consistent with fixed/stationary cylinders, cylinders with two degrees of freedom exhibit a much lower mean Strouhal Number of around 0.14–0.15. Data supports the relationship that Strouhal Number does slightly diminish with increasing Reynolds Number. For oscillating cylinders, the bandwidth about the mean Strouhal Number value appears to remain largely consistent. For many practical structures in the marine environment subject to VIV excitation, such as long span, slender risers, mooring lines, pipeline spans, towed array sonar strings, and alike, the long flexible cylinders will respond in two degrees of freedom, where the identified difference in Strouhal Number is a significant aspect to be accounted for in the modelling of its dynamic behaviour.

scholarly journals Spectral analysis of round jet instabilities at low Reynolds number

2009 ◽  
Vol 10 (6) ◽  
pp. 447-454
Author(s):  
Najah Kechiche ◽  
Ali Abbassi ◽  
Taoufik Filali ◽  
Jacques Jay ◽  
Habib Ben Aissia
Keyword(s):  
Reynolds Number ◽  
Spectral Analysis ◽  
Low Reynolds Number ◽  
Round Jet ◽  
Low Reynolds

Vortex-induced vibrations of a long flexible circular cylinder

1993 ◽  
Vol 250 ◽  
pp. 481-508 ◽  
Author(s):  
D. Brika ◽  
A. Laneville
Keyword(s):  
Circular Cylinder ◽  
Flow Velocity ◽  
Vortex Shedding ◽  
Abrupt Change ◽  
Velocity Range ◽  
End Effects ◽  
Synchronization Region ◽  
Vortex Induced Vibrations ◽  
Set Up ◽  
Vortex Shedding Modes

In an experimental study of the vortex-induced oscillations of a long flexible circular cylinder, the observed stationary amplitudes describe an hysteresis loop partially different from earlier studies. Each branch of the loop is associated with a vortex shedding mode and, as a jump from one branch to the other occurs, the phase difference between the cylinder displacement and the vortex shedding undergoes an abrupt change. The critical flow velocities at which the jump occurs concur with the flow visualization observations of Williamson & Roshko (1988) on the vortex shedding modes near the fundamental synchronization region. Impulsive regimes, obtained at a given flow velocity with the cylinder initially at rest or pre-excited, and progressive regimes resulting from a variation of the flow velocity, are examined. The occurrence of bifurcations is detected for a flow velocity range in the case of the impulsive regimes. The coordinates of the bifurcations define a boundary between two vortex shedding modes, a boundary that verifies the critical curve obtained by Williamson & Roshko (1988). The experimental set-up of this study simulates half the wavelength of a vibrating cable, eliminates the end effects present in oscillating rigid cylinder set-up and has one of the lowest damping ratios reported for the study of this phenomenon.

Fluctuating Temperature Measurements on a Heated Cylinder Placed in a Cylinder Near-Wake

2004 ◽  
Vol 126 (1) ◽  
pp. 62-69 ◽  
Author(s):  
Z. J. Wang ◽  
Y. Zhou ◽  
X. W. Wang ◽  
W. Jin
Keyword(s):  
Hot Wire ◽  
Heat Transfer Characteristics ◽  
Near Wake ◽  
Heated Cylinder ◽  
Fbg Sensor ◽  
Vortex Shedding Frequency ◽  
Sensor Measurement ◽  
Shedding Frequency ◽  
Good Agreement ◽  
Pronounced Peak

The local time-averaged temperature θs¯ and its fluctuating component θs on the surface of a heated circular cylinder immersed in a cylinder near-wake were measured using a fiber-optic Bragg grating (FBG) sensor. Three cylinder center-to-center spacing, i.e., L/d=5.20, 2.50, and 1.18, were investigated. In order to validate the FBG sensor measurement, a thermocouple and a single hot-wire were employed to measure θs¯ on the heated cylinder and streamwise fluctuating velocity u in the near-wake of the downstream cylinder, respectively. The FBG sensor measurement of θs¯ is in good agreement with that simultaneously obtained by the thermocouple. The measured θs is closely correlated to the hot-wire measurement; the θs-spectrum exhibits a pronounced peak at the vortex shedding frequency, as identified in Eu, for each L/d. The results suggest that the FBG sensor can be used to measure reliably both time-averaged and fluctuating temperatures. The heat transfer characteristics of the heated cylinder are examined for different L/d and further compared with the case of an isolated cylinder.

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