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1

Numerical Models for Fatigue Crack Evolution Study

Fuiorea I., Bartis D., Nedelcu R., Frunzulica F.

Fatigue of Aircraft Structures

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2009

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Iss. 1

42--49

EN

The paper presents some considerations regarding to the numerical simulation of the behaviour of the riveted structures in fatigue loading conditions. In order to estimate the stress intensity factor, “k”, different constitutive laws for the materials were considered. Choosing different contours for “J” integral calculation, some simplified models were studied. The final numerical results were analysed with respect to the physical tests.

2

Aeroelastic computation using the beddoes-leishman dynamic stall model

Dumitrescu H., Frunzulica F.

International Journal of Applied Mechanics and Engineering

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2008

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Vol. 13, no 1

63-73

EN

The application of the semi-empirical dynamic stall model by Beddoes and Leishman (B-L) on aeroelastic conditions is described. The approach is to couple the structural model to the nonlinear Beddoes-Leishman model and integrate through time. The nonlinear aerodynamic effects are included in the B-L model and thus, the behavior of the unstable system can be investigated after flutter has occurred, i.e., periodicity (limit cycle oscillations), chaos, etc., can be analyzed. The B-L time integration approach is applied to quickly decide test cases for the unsteady CFO computations, which are much more time consuming. Computations using a NavierStokes solver are compared to the present results.

3

Viscous transonic airfoil flow simulation

Dumitrescu H., Frunzulica F.

International Journal of Applied Mechanics and Engineering

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2004

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Vol. 9, no 4

687-699

EN

A calculation method for the subsonic and transonic viscous flow over airfoil using the displacement surface concept is described. This modelling technique uses a finite volume method for the time-dependent Euler equations and laminar and turbulent boundary-layer integral methods. Additionally special models for transition, laminar or turbulent separation bubbles and trailing edge treatment have been selected. However, the flow is limited to small parts of trailing edge-type separation. Comparisons with experimental data and other methods are shown.