0
Research Papers

Analysis of Supersonic and Transonic Panel Flutter Using a Fluid-Structure Coupling Algorithm

[+] Author and Article Information
Guanhua Mei, Guang Xi, Xu Sun, Jiahui Chen

School of Energy and Power Engineering,
Xi'an Jiaotong University,
Xi'an, Shaanxi 710049, China

Jiazhong Zhang

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

1Corresponding author.

Contributed by the Design Engineering Division of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received March 29, 2013; final manuscript received January 15, 2014; published online April 3, 2014. Assoc. Editor: Massimo Ruzzene.

J. Vib. Acoust 136(3), 031013 (Apr 03, 2014) (11 pages) Paper No: VIB-13-1099; doi: 10.1115/1.4027135 History: Received March 29, 2013; Revised January 15, 2014

In order to analyze the supersonic and transonic panel flutter behaviors quantitatively and accurately, a fluid-structure coupling algorithm based on the finite element method (FEM) is proposed to study the two-dimensional panel flutter problem. First, the Von Kármán's large deformation is used to model the panel, and the high speed airflow is approached by the Euler equations. Then, the equation of panel is discretized spatially by the standard Galerkin FEM, and the equations of fluid are discretized by the characteristic-based split finite element method (CBS-FEM) with dual time stepping; thus, the numerical oscillation encountered frequently in the numerical simulation of flow field could be removed efficiently. Further, a staggered algorithm is used to transfer the information on the interface between the fluid and the structure. Finally, the aeroelastic behaviors of the panel in both the supersonic and transonic airflows are studied in details. And the results show that the system can present the flat and stable, simple harmonic oscillation, buckling, and inharmonic oscillation states at Mach 2, considering the effect of the pretightening force; at Mach 1.2, as the panel loses stability, the ensuing limit cycle oscillation is born; at Mach 0.8 and 0.9, positive and negative bucklings are the typical states of the panel as it loses its stability. Further, the transonic stability boundary is obtained and the transonic bucket is precisely captured. More, this algorithm can be applied to the numerical analysis of other complicated problems related to aeroelasticity.

Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

Schematic of two-dimensional panel flutter

Grahic Jump Location
Fig. 2

Computational domain of flow field

Grahic Jump Location
Fig. 3

Full view of mesh for flow field

Grahic Jump Location
Fig. 4

Partial view of mesh for flow field

Grahic Jump Location
Fig. 5

Verification of moving mesh method (mesh for flow over a curved panel of w=0.05asin(2πx/a))

Grahic Jump Location
Fig. 6

Grid-independence analysis of flow field

Grahic Jump Location
Fig. 7

Grid-independence analysis of panel structure

Grahic Jump Location
Fig. 21

Time history of displacement of a limit cycle oscillation (Ma∞ = 1.2, λ* = 100, ρ¯ = 0.1)

Grahic Jump Location
Fig. 9

Time history of displacement of a flat and stable state (Ma∞ = 2, ρ¯ = 0.02, R = 0, λ = 300)

Grahic Jump Location
Fig. 10

Time history of displacement of a simple harmonic oscillation (Ma∞ = 2, ρ¯ = 0.02, R = 0, λ = 500)

Grahic Jump Location
Fig. 13

Effect of λ on maximum and minimum displacements of limit cycle oscillations (Ma∞ = 2, ρ¯ = 0.02, R = 0)

Grahic Jump Location
Fig. 14

Time history of displacement of a system in buckling (Ma∞ = 2, ρ¯ = 0.02, R = 2, λ = 50)

Grahic Jump Location
Fig. 15

Deflection of a buckled panel (Ma∞ = 2, ρ¯ = 0.02, R = 2, λ = 50)

Grahic Jump Location
Fig. 16

Pressure distribution over a buckled panel (Ma∞ = 2, ρ¯ = 0.02, R = 2, λ = 50)

Grahic Jump Location
Fig. 17

Steady state response of an inharmonic oscillation (Ma∞ = 2, ρ¯ = 0.02, R = 5, λ = 140)

Grahic Jump Location
Fig. 18

Phase portrait of an inharmonic oscillation system (Ma∞ = 2, ρ¯ = 0.02, R = 5, λ = 140)

Grahic Jump Location
Fig. 19

Spectrum analysis of an inharmonic oscillation system (Ma∞ = 2, ρ¯ = 0.02, R = 5, λ = 140)

Grahic Jump Location
Fig. 8

Analysis of time step independence in presented algorithm for fluid-structure interaction

Grahic Jump Location
Fig. 11

Instantaneous panel deformation in one period (Ma∞ = 2, ρ¯ = 0.02, R = 0, λ = 500)

Grahic Jump Location
Fig. 12

Instantaneous aerodynamic loads over panel in one period (Ma∞ = 2, ρ¯ = 0.02, R = 0, λ = 500)

Grahic Jump Location
Fig. 20

Stability regions (Ma∞ = 2, ρ¯ = 0.02)

Grahic Jump Location
Fig. 22

Amplitude of limit cycle as function of dynamic pressure (Ma∞ = 1.2, ρ¯ = 0.1)

Grahic Jump Location
Fig. 23

Time history of deformation of buckling panel in positive direction (Ma∞ = 0.9, h/a = 0.004, aluminum panel at sea level)

Grahic Jump Location
Fig. 24

Buckling shape of panel in positive direction (Ma∞ = 0.9, h/a = 0.004, aluminum panel at sea level)

Grahic Jump Location
Fig. 25

Time history of deformation of buckling panel in negative direction (Ma∞ = 0.9, h/a = 0.004, aluminum panel at sea level)

Grahic Jump Location
Fig. 26

Buckling shape of panel in negative direction (Ma∞ = 0.9, h/a = 0.004, aluminum panel at sea level)

Grahic Jump Location
Fig. 27

Effect of h/a on peak buckling deformation at Ma∞ = 0.8

Grahic Jump Location
Fig. 28

Effect of h/a on peak buckling deformation at Ma∞ = 0.9

Grahic Jump Location
Fig. 29

Stability boundary (ρ¯ = 0.1)

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In