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Research Papers

Analysis of Curved Panel Flutter in Supersonic and Transonic Airflows Using a Fluid–Structure Coupling Algorithm

[+] Author and Article Information
Guanhua Mei

School of Energy and Power Engineering,
Jiangsu University,
Zhenjiang 212013, Jiangsu, China
e-mail: meiguanhua@ujs.edu.cn

Jiazhong Zhang

School of Energy and Power Engineering,
Xi'an Jiaotong University,
Xi'an 710049, Shaanxi, China
e-mail: jzzhang@mail.xjtu.edu.cn

Can Kang

School of Energy and Power Engineering,
Jiangsu University,
Zhenjiang 212013, Jiangsu, China
e-mail: kangcan@ujs.edu.cn

1Corresponding author.

Contributed by the Technical Committee on Vibration and Sound of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received March 4, 2016; final manuscript received February 2, 2017; published online May 30, 2017. Assoc. Editor: Marco Amabili.

J. Vib. Acoust 139(4), 041004 (May 30, 2017) (13 pages) Paper No: VIB-16-1105; doi: 10.1115/1.4036103 History: Received March 04, 2016; Revised February 02, 2017

In order to accurately study the effect of curvature on panel aeroelastic behaviors, a fluid–structure coupling algorithm is adopted to analyze the curved panel flutter in transonic and supersonic airflows. First, the governing equation for the motion of the curved panel and the structure solver are presented. Then, the fluid governing equations, the fluid solver, and the fluid–structure coupling algorithm are introduced briefly. Finally, rich aeroelastic responses of the curved panel are captured using this algorithm. And the mechanisms of them are explored by various analysis tools. It is found that the curvature produces initial aerodynamic loads above the panel. Thus, the static aeroelastic deformation exists for the curved panel in stable state. At Mach 2, with its stability lost on this static aeroelastic deformation, the curved panel shows asymmetric flutter. At Mach 0.8 and 0.9, the curved panel exhibits only positive static aeroelastic deformation due to this initial aerodynamic load. At Mach 1.0, as the dynamic pressure increases, the curved panel loses its static and dynamic stability in succession, and behaves as static aeroelastic deformations, divergences, and flutter consequentially. At Mach 1.2, with its stability lost, the curved panel flutters more violently toward the negative direction. The results obtained could guide the panel design and panel flutter suppression for flight vehicles with high performances.

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References

Figures

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Fig. 1

Schematic of two-dimensional curved panel flutter

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Fig. 2

Computational domain for flow field

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Fig. 3

Mesh for flow field: (a) full view and (b) partial view

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Fig. 4

Time history of curved panel in static aeroelastic deformation state (Ma∞=2, ρ¯=0.2, H/h = 1, and λ=200)

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Fig. 5

Pressure contours above curved panel (Ma∞=2, ρ¯=0.2, H/h = 1, and λ=200): (a) initial curved panel and (b) finial curved panel with static aeroelastic deformation

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Fig. 6

Effect of λ on static aeroelastic behavior of curved panels (Ma∞=2, ρ¯=0.2, and H/h = 1): (a) stable deformations and (b) pressure coefficients

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Fig. 7

Curved panel in periodic flutter (Ma∞=2, ρ¯=0.2, H/h = 1, and λ=300): (a) time history, (b) panel deflection with space and time, and (c) transient panel shape

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Fig. 8

POD modes analysis of curved panel in periodic flutter (Ma∞=2, ρ¯=0.2, H/h = 1, and λ=300): (a) POD modes and (b) energy percentage of each POD mode

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Fig. 9

Effect of λ on positive and negative peak amplitudes of curved panel flutter (Ma∞=2, ρ¯=0.2, and H/h = 1)

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Fig. 10

Chaotic motion of curved panel (Ma∞=2, ρ¯=0.2, H/h = 2, and λ=200): (a) time history, (b) spectrum diagram, and (c) panel deflection with space and time

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Fig. 11

POD modes analysis of curved panel in chaotic flutter (Ma∞=2, ρ¯=0.2, H/h = 2,and λ=200): (a) POD modes and (b) energy percentage of each POD mode

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Fig. 12

Time history of displacement for curved panel in periodic oscillation (Ma∞=2, ρ¯=0.2, H/h = 2, and λ=400)

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Fig. 13

Bifurcation diagram of maximum panel deflection against λ (Ma∞=2, ρ¯=0.2, and H/h = 2): (a) piston theory and (b) present algorithm

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Fig. 14

Flutter dynamic pressure λcr versus plate rise H/h (Ma∞=2 and ρ¯=0.2)

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Fig. 15

Curved panel in static aeroelastic deformation (aluminum panel at sea level, Ma∞=0.8, h/a = 0.002, and H/h = 1): (a) finial deformation and aerodynamic load and (b) pressure contour of flow field

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Fig. 16

Effect of h/a and H/h on stable deformation of curved panels (aluminum panel at sea level): (a) Ma∞=0.8 and (b) Ma∞=0.9

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Fig. 17

Static aeroelastic deformation of curved panel after divergence (Ma∞=1.0, ρ¯=0.1, and H/h = 1)

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Fig. 18

Curved panel in inharmonic flutter (Ma∞=1.0, ρ¯=0.1, H/h = 1, and λ∗=82): (a) time history, (b) phase-space evolution, (c) spectrum diagram, and (d) panel deflection with space and time

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Fig. 19

POD modes analysis of curved panel in inharmonic flutter (Ma∞=1.0, ρ¯=0.1, H/h = 1, and λ∗=82): (a) POD modes and (b) energy percentage of each POD mode

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Fig. 20

Bifurcation diagram of maximum panel deflection (Ma∞=1.0, ρ¯=0.1, and H/h = 1)

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Fig. 21

Curved panel in periodic flutter (Ma∞=1.2, ρ¯=0.1, H/h = 1, and λ∗=100): (a) time history, (b) spectrum analysis, and (c) panel deflection with space and time

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Fig. 22

POD modes analysis of curved panel in periodic flutter (Ma∞=1.2, ρ¯=0.1, H/h = 1, and λ∗=100): (a) POD modes and (b) energy percentage of each POD mode

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Fig. 23

Effect of λ∗ on flutter amplitude of curved panel (Ma∞=1.2, ρ¯=0.1, and H/h = 1)

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Fig. 24

Stability boundary of curved panel (ρ¯=0.1): (a) H/h = 0 and (b) H/h = 1

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