Experimental observation of single mode panel flutter in supersonic gas flow

Vedeneev, Vasily; Guvernyuk, S. V.; Zubkov, A. F.; Kolotnikov, M. E.

doi:10.1016/j.jfluidstructs.2010.04.004

Cited by 30 publications

(10 citation statements)

References 20 publications

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“…(This e¨ect does not appear for the modes 1; 1 and 1; 3 as they have an odd number in the transversal direction too or for mode 1; 2 as its frequency is very close to the frequency of mode 2; 0.) In comparison with Vedeneev et al [6], much more and also higher modes could be surely identi¦ed. A detailed discussion of the di¨erences is given in subsection 6.3.…”

Section: Flow Structure Interactionmentioning

confidence: 62%

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Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow

Willems

Gülhan

Esser

2013

Progress in Flight Physics

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Since escalating §uid structure interactions (FSI) can cause a complete loss of a spacecraft, a detailed knowledge of the mechanisms of §ow structure interactions in supersonic §ows is important for the design of future space transportation systems. The ¦rst step is to analyze the basic mechanisms at a generic test case that is ascertainable also with high quality simulations. Therefore, this work was devoted to the investigation of the shock wave boundary layer interaction on an elastic panel. During the wind tunnel experiments, the panel de §ection was measured with fast nonintrusive displacement sensors. On the §ow side pressure, high-speed Schlieren photography and oil-¦lm technique were used. The §ow manipulation due to the panel de §ection becomes manifest in a deformation of the impinging shock and the separation zone. The panel de §ection consists of a constant and a dynamic component. The experimental results are discussed and compared to numerical results.

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Section: Flow Structure Interactionmentioning

confidence: 62%

“…A key factor for the nozzle design is the comprehension of the §uid structure interactions in supersonic §ows [1,2]. Therefore, it was the topic of several numerical [3,4] and experimental investigations [5,6].…”

Section: Introductionmentioning

confidence: 99%

Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow

Willems

Gülhan

Esser

2013

Progress in Flight Physics

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“…Dowell and coworkers [11][12][13][14] have done extensive numerical simulation of the panel flutter and mechanics of this problem. See also recent research results that have been obtained in the last decade in works of Vedeneev et al [15][16][17][18][19].…”

Section: Introductionmentioning

confidence: 88%

Direct Numerical Simulation of the Airfoil Segment's Flutter and its Effect on the Aerodynamic Force

Zelenyy¹

2017

ujam

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This article presents numerical simulation of planar potential flow around an airfoil with possibility of changing its shape. Two-dimensional unsteady flow model with scalar velocity potential, which allows us to calculate pressure distribution along an airfoil from Cauchy-Lagrange integral, is used. For this purpose, an airfoil contour is approximated by a complex cubic spline with possibility of displacement its vertices. This algorithm has been used in the context of fluid-structure interaction and has been applied successfully to determination of stability of an elastic airfoil segment interacting with a flow stream, so-called panel flutter problem. Calculation of external flow is carried out by vortex panel method with Kutta-Joukowski trailing edge condition, which makes mathematical solution unique. Using this method of approximation of an airfoil in combination with the method of discrete vortices provides a semi-analytical solution for complex potential for whole computational domain of air flow. This solution significantly accelerates process of numerical computation of time-averaged aerodynamic force as well as the dynamic stability problem for aeroelastic wing design and temporal evolution of its natural disturbances.

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“…Experimental studies of plates have been conducted across a wide range of Mach numbers 10 and have predominantly focussed on the structural response of the plate. This ties in with the limit cycle studies of Dowell 5 and Visbal 9 however the analysis of the flow structure was not investigated in such great detail.…”

Section: Introductionmentioning

confidence: 99%

Wind Tunnel Experiments with Flexible Plates in Transonic Flows

Jinks

Bruce

Santer

2016

54th AIAA Aerospace Sciences Meeting

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The evolution of adaptive shock control bump (SCB) design has seen the system flexibility increase to a point where the aerodynamic loading can affect the deformation of the plate. By studying the effects of a flexible plate subject to transonic flow the fluid structure interaction can be investigated. In this study an array of thin plates (0.4 and 0.6 mm) with different aspect ratios (1 and 1.33) are exposed to a Mach 1.4 normal shockwave. PIV is used in combination with Schlieren imaging to provide a detailed view of the flow curvature surrounding the plate as well as the global shock structure. A technique that extracts the plate deformation from the PIV images is also presented which provides fluid and structural information for each test. The relationship between plate and flow angle is discussed as well as the effect of plate stiffness and free stream influence of each plate configuration.

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Experimental observation of single mode panel flutter in supersonic gas flow

Cited by 30 publications

References 20 publications

Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow

Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow

Direct Numerical Simulation of the Airfoil Segment's Flutter and its Effect on the Aerodynamic Force

Wind Tunnel Experiments with Flexible Plates in Transonic Flows

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