Aeroelastic Stability of Cylindrical Shells in Supersonic Flow with Boundary Layer

Alder, Marko

doi:10.2514/6.2017-3618

Cited by 1 publication

(1 citation statement)

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“…Sabri and Lakis utilized an axisymmetric shell finite element developed on the basis of Sanders' thin‐shell theory in which the displacement fields were determined from the exact solution of the shell governing equations to investigate the supersonic flutter of a circular cylindrical shell under internal pressure and axial compression load. Alder addressed the effect of a turbulent boundary layer on the supersonic flutter of a circular cylindrical shell by using a high‐fidelity fluid‐structure model in which the MSC Nastran finite element solver was coupled with the Navier‐Stokes solver DLR‐Tau. Klock and Cesnik studied the aeroelastic response of a pressurized circular cylindrical shell subjected to axial flow at Mach 3 using a nonlinear transient FEM on the basis of ABAQUS FEM/CAE software and the third‐order piston theory.…”

Section: Introductionmentioning

confidence: 99%

Sloshing effects on supersonic flutter characteristics of a circular cylindrical shell partially filled with liquid

Zarifian

Ovesy

Firouz-Abadi

2018

Numerical Meth Engineering

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Summary This paper aims to revisit the effect of sloshing on the flutter characteristics of a partially liquid‐filled cylinder. A computational fluid‐structure interaction model within the framework of the finite element method is developed to capture fluid‐structure interactions arising from the sloshing of the internal fluid and the flexibility of its containing structure exposed to an external supersonic airflow. The internal liquid sloshing is represented by a more sophisticated model, referred to as the liquid sloshing model, and the shell structure is modeled by Sanders' shell theory. The aerodynamic pressure loading is approximated by the first‐order piston theory. The initial geometric stiffness due to prestresses in the initial configuration stemming from the fluid hydrostatic pressure, internal pressure, and axial compression load is also considered. The obtained results reveal that the sloshing of the internal fluid has little influence on the supersonic flutter boundary of a cylinder partially filled with liquid, at least for the case considered here. It is also shown that the critical freestream static pressure predicted by the sloshing model is negligibly larger than that calculated by the hydroelastic model of the internal fluid, which means that the sloshing of the internal fluid slightly overestimates the flutter boundary.

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Section: Introductionmentioning

confidence: 99%