Computational aeroelastic simulations of self-sustained pitch oscillations of a NACA0012 at transitional Reynolds numbers

Poirel, Dominique; Métivier, Vincent; Dumas, Guy

doi:10.1016/j.jfluidstructs.2011.05.009

Cited by 66 publications

(32 citation statements)

References 13 publications

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“…[33]). Using such high-order computational methods, Poirel et al [34] have studied limit-cycle oscillations caused by laminar separation bubbles at transitional Reynolds numbers, and Sváček et al [35] have studied LCOs at high Reynolds numbers. Peng & Zhu [36] have used a similar framework to assess energy extraction from oscillating structures.…”

Section: Introductionmentioning

confidence: 99%

Limit-cycle oscillations in unsteady flows dominated by intermittent leading-edge vortex shedding

Ramesh

Murua

Gopalarathnam

2015

Journal of Fluids and Structures

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High-frequency limit-cycle oscillations of an airfoil at low Reynolds number are studied numerically. This regime is characterized by large apparentmass effects and intermittent shedding of leading-edge vortices. Under these conditions, leading-edge vortex shedding has been shown to result in favorable consequences such as high lift and efficiencies in propulsion/power extraction, thus motivating this study. The aerodynamic model used in the aeroelastic framework is a potential-flow-based discrete-vortex method, augmented with intermittent leading-edge vortex shedding based on a leadingedge suction parameter reaching a critical value. This model has been validated extensively in the regime under consideration and is computationally cheap in comparison with Navier-Stokes solvers. The structural model used has degrees of freedom in pitch and plunge, and allows for large amplitudes and cubic stiffening. The aeroelastic framework developed in this paper is employed to undertake parametric studies which evaluate the impact of different types of nonlinearity. Structural configurations with pitch-to-plunge frequency ratios close to unity are considered, where the flutter speeds are lowest (ideal for power generation) and reduced frequencies are highest. The range of reduced frequencies studied is two to three times higher than most airfoil studies, a virtually unexplored regime. Aerodynamic nonlinearity re- * Corresponding authorEmail addresses: kiran.ramesh@glasgow.ac.uk (Kiran Ramesh), j.murua@surrey.ac.uk (Joseba Murua), agopalar@ncsu.edu (Ashok Gopalarathnam) Fluids and Structures February 10, 2015 sulting from intermittent leading-edge vortex shedding always causes a supercritical Hopf bifurcation, where limit-cycle oscillations occur at freestream velocities greater than the linear flutter speed. The variations in amplitude and frequency of limit-cycle oscillations as functions of aerodynamic and structural parameters are presented through the parametric studies. The excellent accuracy/cost balance offered by the methodology presented in this paper suggests that it could be successfully employed to investigate optimum setups for power harvesting in the low-Reynolds-number regime. Preprint submitted to Journal of

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Section: Introductionmentioning

confidence: 99%

Limit-cycle oscillations in unsteady flows dominated by intermittent leading-edge vortex shedding

Ramesh

Murua

Gopalarathnam

2015

Journal of Fluids and Structures

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“…Although the range of Re for the modern HAWT can be as high as 2 Â 10 6 (Hansen and Butterfield, 1993), or even higher for some MW scale turbines, for small-to-medium sized VAWTs, such as the recently rising H-type Darrieus turbines, it is common to operate with Re of the order 10 5 or even lower (Sheldahl et al, 1980). Flows with such relatively low Reynolds number are highly non-linear (Poirel et al, 2011) and deep stall are often associated with leading edge separation and in particular, boundary layer transitions from laminar to turbulent flows, which are very sensitive to local adverse pressure gradients as well as the advection scheme and turbulence model employed. This makes accurate predictions of the flow separation and the onset of the dynamic stall much more difficult.…”

Section: Introductionmentioning

confidence: 99%

Turbulence modeling of deep dynamic stall at relatively low Reynolds number

Wang

Ingham

et al. 2012

Journal of Fluids and Structures

163

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“…For instance, cable-stayed bridges can experience large amplitude vibration attributed to galloping of dry inclined cables induced at critical Reynolds number (Macdonald and Larose, 2005;Kleissl and Georgakis, 2011), NACA0012 wing can flutter due to flow separation (Poirel et al, 2011), heatexchanger tubes can rupture, and ICI nozzles and guide tubes in a PWR-type nuclear reactor can break by lock-in (Païdoussis, 2006). Moreover, a heavy-lift launch vehicle (such as a space rocket or space shuttle) can respond to buffeting caused by alternate vortex-pair shedding (Dotson and Engblom, 2004).…”

Section: Introductionmentioning

confidence: 99%

Numerical quantification of aerodynamic damping on pitching of vehicle-inspired bluff body

Cheng¹,

Tsubokura²,

Nakashima³

et al. 2012

Journal of Fluids and Structures

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The influence of transient flows on vehicle stability was investigated by large eddy simulation. To consider the dynamic response of a vehicle to real-life transient aerodynamics, a dimensionless parameter that quantifies the amount of aerodynamic damping for vehicle subjects to pitching oscillation is proposed. Two vehicle models with different stability characteristics were created to verify the parameter. For idealized notchback models, underbody has the highest contribution to the total aerodynamic damping, which was up to 69%. However, the difference between the aerodynamic damping of models with distinct A-and C-pillar configurations mainly depends on the trunk-deck contribution. Comparison between dynamically obtained phase-averaged pitching moment with quasisteady values shows totally different aerodynamic behaviors.

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Computational aeroelastic simulations of self-sustained pitch oscillations of a NACA0012 at transitional Reynolds numbers

Cited by 66 publications

References 13 publications

Limit-cycle oscillations in unsteady flows dominated by intermittent leading-edge vortex shedding

Limit-cycle oscillations in unsteady flows dominated by intermittent leading-edge vortex shedding

Turbulence modeling of deep dynamic stall at relatively low Reynolds number

Numerical quantification of aerodynamic damping on pitching of vehicle-inspired bluff body

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