Experiments on heave/pitch limit-cycle oscillations of a supercritical airfoil close to the transonic dip

Dietz, G.; Schewe, G.; Mai, Holger

doi:10.1016/j.jfluidstructs.2003.07.019

Cited by 47 publications

(32 citation statements)

References 19 publications

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“…It was shown that modeling the wind-tunnel wall porosity significantly affects the LCO characteristics. These results confirmed the authors' former decision to avoid this additional challenge in simulation by providing well-defined boundary conditions in terms of an adaptive test section (Wedemeyer et al, 1998) for the recent experiments (torsion flutter in Schewe et al, 2002;Dietz et al, 2004a). Thomas et al (2003) simulated the torsion flutter in transonic flow observed by Schewe et al (2002) in the adaptive test section.…”

Section: Recent Progresses In Understanding Transonic Aeroelasticitysupporting

confidence: 77%

“…morphing airplanes Schuster et al, 2003). Therefore, in a previous paper, the authors linked the global aerodynamic force behavior to observed transonic-dip phenomena and LCOs (Dietz et al, 2004a). In the present paper, the authors' goal is to provide a more detailed understanding of the local aerodynamic phenomena that cause both the amplification and the amplitude limitation of aeroelastic oscillations close to the transonic dip.…”

Section: Introductionmentioning

confidence: 93%

“…The disagreement was suspected to be caused by viscous effects which could not be taken into account by the Euler HB method, although the experiments indicate strong shock-induced separation at these conditions. The authors presumed that arranging the steady flowfield appropriately may cause unsteady flow that does not lead to a pronounced transonic dip (Dietz et al, 2004a). This idea was investigated by Dietz et al (2004b): a computational lift-constrained airfoil-shape optimization was conducted with the two objectives to minimize the drag as well as the upstream propagation time of pressure disturbances in the steady flowfield above the airfoil for a given transonic Mach number and a given Reynolds number.…”

Section: Recent Progresses In Understanding Transonic Aeroelasticitymentioning

confidence: 99%

See 2 more Smart Citations

Amplification and amplitude limitation of heave/pitch limit-cycle oscillations close to the transonic dip

Dietz¹,

Schewe²,

Mai³

2006

Journal of Fluids and Structures

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Section: Recent Progresses In Understanding Transonic Aeroelasticitysupporting

confidence: 77%

Section: Introductionmentioning

confidence: 93%

Section: Recent Progresses In Understanding Transonic Aeroelasticitymentioning

confidence: 99%

See 1 more Smart Citation

Amplification and amplitude limitation of heave/pitch limit-cycle oscillations close to the transonic dip

Dietz¹,

Schewe²,

Mai³

2006

Journal of Fluids and Structures

Self Cite

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“…Self-sustained oscillations are typically stable and the frequency of motion is determined by the properties of the system itself; the motion is maintained by an internal source of energy that compensates dissipation in the system. Common examples of engineered systems in which limit cycle dynamics play an important role, (and which may provide insight into oscillating wing propulsion) include underwater structures and cables [29] and flutter in aircraft wings and helicopter blades [69,70].…”

Section: Forced and Passive Leading Edge Vortex Controlmentioning

confidence: 99%

Fluid mechanics of flapping wings

Ellenrieder

Parker

Soria

2008

Experimental Thermal and Fluid Science

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“…The pitch movement around the elastic axis is represented by the angle of attack α and the plunge movement relative to the horizontal surface is denoted by h. The NLR 7301 airfoil section aero-elastic model was tested intensively by Dietz et al [9] and the model parameters are presented in their articles. Transonic aeroelastic experiments in wind tunnel were conducted for various Mach numbers and angles of attack, and LCO was observed in some special instances.…”

Section: Nlr 7301 Airfoil Modelmentioning

confidence: 99%

A nonlinear POD reduced order model for limit cycle oscillation prediction

Chen

Yan

2010

Sci. China Phys. Mech. Astron.

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As the amplitude of the unsteady flow oscillation is large or large changes occur in the mean background flow such as limit cycle oscillation, the traditional proper orthogonal decomposition reduced order model based on linearized time or frequency domain small disturbance solvers can not capture the main nonlinear features. A new nonlinear reduced order model based on the dynamically nonlinear flow equation was investigated. The nonlinear second order snapshot equation in the time domain for proper orthogonal decomposition basis construction was obtained from the Taylor series expansion of the flow solver. The NLR 7301 airfoil configuration and Goland+ wing/store aeroelastic model were used to validate the capability and efficiency of the new nonlinear reduced order model. The simulation results indicate that the proposed new reduced order model can capture the limit cycle oscillation of aeroelastic system very well, while the traditional proper orthogonal decomposition reduced order model will lose effectiveness. reduced-order model, limit cycle oscillation, proper orthogonal decomposition, aeroelasticity PACS: 47.52.+j, 47.40.Hg With the development of computational aeroelasticity, the aeroelastic response can be accurately predicted by the high-fidelity physics-based mathematical model such as computational fluid dynamics (CFD) and computational structure dynamics (CSD) couple solver. However, the computation cost is too large for these high-fidelity methods to be applied to the multidisciplinary conception design with many iterations. Unlike high-fidelity couple solver, the reduced order model (ROM) aims to construct a simple mathematical representation model, which can capture the dominating behavior of aeroelastic system and can be conveniently used in conception design, control and data-driven systems [1].Many approaches for constructing linear flow based aeroelastic ROMs have been developed and were shown to produce numerical results which compare well with highfidelity nonlinear solver. Among these approaches, the reduced order model based on proper orthogonal decomposition (POD/ROM)has become the most popular method. For example, the POD/ROM was successfully applied to the CFD-based aeroelastic analysis of airfoil [2], wing [3] and full aircraft [4], especially in flutter prediction [3][4][5]. Most of the currently proposed ROMs are typically constructed based on the linearized time or frequency domain small disturbance solvers, which are dynamically linearized about the nonlinear steady mean background flow.Most aeroelastic phenomena such as flutter and gust response can be dealt with these ROMs based on dynamically linearization methods. But unfortunately, some important strong nonlinear dynamics with large structure deformation can not be simulated by the small disturbance solvers, for example, limit cycle oscillation (LCO) [6,7]. There are seldom successful reports about the traditional time-domain POD/ROM to predict LCO generated by nonlinear aerodynamics. Although the first order frequency-do...

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Experiments on heave/pitch limit-cycle oscillations of a supercritical airfoil close to the transonic dip

Cited by 47 publications

References 19 publications

Amplification and amplitude limitation of heave/pitch limit-cycle oscillations close to the transonic dip

Amplification and amplitude limitation of heave/pitch limit-cycle oscillations close to the transonic dip

Fluid mechanics of flapping wings

A nonlinear POD reduced order model for limit cycle oscillation prediction

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