Simulation of 2D fluid–structure interaction in inviscid compressible flows using a cell-vertex central difference finite volume method

Hejranfar, Kazem; Azampour, Mohammad-Hadi

doi:10.1016/j.jfluidstructs.2016.09.009

Cited by 18 publications

(4 citation statements)

References 36 publications

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“…Therefore, this article studies the transonic regime up to Mach number 0.9. However, similar to other studies, 11,39,40,43,44 this study also shows rational results for low amplitude oscillation.…”

Section: Resultssupporting

confidence: 91%

“…22 The present investigation considers inviscid flow around the NACA0012 airfoil with a linear structure and at zero incidence. Many researchers 11,14,39,40 use Euler equations for their aerodynamic part. Since this study solves Euler equations for the aerodynamic part, the only source of nonlinearity is the compressibility effects in the transonic regime.…”

Section: Resultsmentioning

confidence: 99%

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Simulating aeroelastic response of a self-sustained oscillating rigid airfoil using a boundary oscillation method

Araghizadeh

Djavareshkian

Rezaeepazhand

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The present study presents a new nonlinear unsteady aerodynamic model to investigate the aeroelastic behavior of a self-sustained oscillating rigid airfoil. Here the unsteady Euler equations are considered simulating inviscid compressible transonic flow over an oscillating airfoil. In regard to providing boundedness criteria, a high-order technique based on a normalized variable diagram scheme has been presented. Since using dynamic mesh for simulating flow over a dynamic airfoil is too complex and requires many computational efforts, the current paper proposes a nonorthogonal and static mesh with oscillation of flow boundary. The results are compared with both well-validated numerical methods and experimental data. A time-marching method is employed to determine system responses. The predicted flutter boundary for NACA0012 airfoil at different free-stream Mach numbers is in fair agreement with direct flutter tools of the Hopf bifurcation points. Finally, the influences of the center of mass and elastic axis position on the system aeroelastic behavior are examined.

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Section: Resultssupporting

confidence: 91%

Section: Resultsmentioning

confidence: 99%

Simulating aeroelastic response of a self-sustained oscillating rigid airfoil using a boundary oscillation method

Araghizadeh

Djavareshkian

Rezaeepazhand

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…• multi-physics and fluid-solid interaction [189,192,195,200,201,203,207,215,218,222,228,235,245,247,248,250,252,263,272];…”

Section: Vertex-based Fv Methodsmentioning

confidence: 99%

Thirty years of the finite volume method for solid mechanics

Cardiff,

Demirdžić

2018

Preprint

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Since early publications in the late 1980s and early 1990s, the finite volume method has been shown suitable for solid mechanics analyses. At present, there are several flavours of the method, including "cell-centred", "staggered", "vertex-centred", "periodic heterogenous microstructural", "Godunov-type", "matrix-free", "meshless", as well as others. This article gives an overview, historical perspective, comparison and critical analysis of the different approaches, including their relative strengths, weaknesses, similarities and dissimilarities, where a close comparison with the de facto standard for computational solid mechanics, the finite element method, is given. The article finishes with a look towards future research directions and steps required for finite volume solid mechanics to achieve widespread acceptance.

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“…This classical panel flutter problem has been studied in the 1950-1970s in numerous papers, where linear piston theory was employed for modeling high-speed supersonic flow [6][7][8][9][10][11]. The interest in this problem was renewed in the 2000s, when several aeroelastic solvers based on full Euler or Reynolds-averaged Navier-Stokes equations were developed by different groups and showed their capability of solving the panel flutter problem at transonic and low supersonic speed in linear [12,13] and nonlinear [5,[14][15][16][17][18][19][20][21] formulations.…”

Section: Introductionmentioning

confidence: 99%

Transonic Panel Flutter in Accelerating or Decelerating Flow Conditions

Shishaeva¹,

Vedeneev²,

Aksenov³

et al. 2018

AIAA Journal

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Nonlinear panel flutter oscillations at transonic and low supersonic flow speed demonstrate rich panel dynamics, which includes bifurcations of the limit cycle, coexisting of different limit cycles, and nonperiodic oscillations. Passing through the range of transonic Mach numbers to supersonic cruise speed should be sufficiently fast to avoid significant fatigue damage. In this study, the sequence of bifurcations of limit cycles when the flow speed is continuously increasing or decreasing is analyzed. The evolution of limit-cycle oscillations is carefully studied. It is shown that the most dangerous oscillation regimes, high-frequency periodic or nonperiodic oscillations, are suppressed if the flow acceleration is sufficiently fast. However, first-mode limit cycle and limit cycle involving internal 1:2 resonance are not affected by the flow acceleration, such that lower accumulation of the fatigue damage in fast accelerating flow is possible only because of fewer cycles of oscillations, but not because of the decrease of the limit-cycle amplitude.

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Simulation of 2D fluid–structure interaction in inviscid compressible flows using a cell-vertex central difference finite volume method

Cited by 18 publications

References 36 publications

Simulating aeroelastic response of a self-sustained oscillating rigid airfoil using a boundary oscillation method

Simulating aeroelastic response of a self-sustained oscillating rigid airfoil using a boundary oscillation method

Thirty years of the finite volume method for solid mechanics

Transonic Panel Flutter in Accelerating or Decelerating Flow Conditions

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