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De Jong, A.T. (author), Bijl, H. (author)
Cavity aeroacoustic noise is relevant for aerospace and automotive industries and widely investigated since the 1950’s. Most investigations so far consider cavities where opening length and width are of similar scale. The present investigation focuses on a less investigated setup, namely cavities that resemble the door gaps of automobiles. These...
conference paper 2010
document
Witteveen, J.A.S. (author), Bijl, H. (author)
A monomial chaos approach is proposed for efficient uncertainty quantification in nonlinear computational problems. Propagating uncertainty through nonlinear equations can still be computationally intensive for existing uncertainty quantification methods. It usually results in a set of nonlinear equations which can be coupled. The proposed...
conference paper 2006
document
Witteveen, J.A.S. (author), Bijl, H. (author)
conference paper 2008
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Deng, S. (author), Van Oudheusden, B.W. (author), Remes, B.D.W. (author), Persin, M. (author), Bijl, H. (author), Ruijsink, H.M. (author)
conference paper 2013
document
Van Zuijlen, A.H. (author), Bijl, H. (author)
Computational fluid-structure interaction is commonly performed using a partitioned approach. For strongly coupled problems sub-iterations are required, increasing computational time as flow and structure have to be resolved multiple times every time step. Reductions in computing times can be achieved by e.g. improving the convergence of the sub...
conference paper 2011
document
De Boer, A. (author), Van der Schoot, M.S. (author), Bijl, H. (author)
A new point-by-point mesh movement algorithm is developed for the deformation of unstructured grids. The method is based on using radial basis function, RBFs, to interpolate the displacements of the boundary nodes to the whole flow mesh. A small system of equations has to be solved, only involving the nodes on the boundary of the flow domain....
conference paper 2006
document
Loeven, G.J.A. (author), Bijl, H. (author)
In this paper the Probabilistic Collocation method is used for uncertainty quantification of operational uncertainties in a transonic axial flow compressor (i.e. NASA Rotor 37). Compressor rotors are components of a gas turbine that are highly sensitive to operational and geometrical uncertainties. Validation of the Probabilistic Collocation...
conference paper 2010
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Noyon, T.A. (author), Tay, W.B. (author), Van Oudheusden, B.W. (author), Bijl, H. (author)
A three-dimensional simulation of hovering flapping wings was performed using an immersed boundary method. This was done to investigate the effects of chordwise wing deformation on three important unsteady aerodynamic mechanisms found in flapping flight, namely Leading Edge Vortex (LEV) shedding, wake capture and clap and fling. A wing was...
conference paper 2014
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Bijl, H. (author), Wesseling, P. (author)
conference paper 1997
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Loeven, A. (author), Witteveen, J.A.S. (author), Bijl, H. (author)
In this paper a Two Step approach with Chaos Collocation for efficient uncertainty quantification in computational fluid-structure interactions is followed. In Step I, a Sensitivity Analysis is used to efficiently narrow the problem down from multiple uncertain parameters to one parameter which has the largest influence on the solution. In Step...
conference paper 2006
document
Sarkar, S. (author), Bijl, H. (author)
In this paper the aeroelastic stability of a wind turbine rotor in the dynamic stall regime is investigated. Increased flexibility of modern turbine blades makes them more susceptible to aeroelastic instabilities. Complex oscillation modes like flap/lead-lag are of particular concern, which give way to potential structural damage, see...
conference paper 2006
document
Kazemi Kamyab, V. (author), Van Zuijlen, A.H. (author), Bijl, H. (author)
The application of higher order implicit time integration schemes to conjugate heat transfer problems is analyzed with Dirichlet-Neumann as the decomposition method. In the literature, only up to second order implicit time integration schemes have been reported while there is a potential for gaining computational efficiency using higher orders....
conference paper 2011
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Gillebaart, T. (author), Van Zuijlen, A.H. (author), Bijl, H. (author)
In this paper, the influence of wing flexibility and the 'clap-and-peel' motion (one versus two wings) on the upward (lifting) force in hover is studied. CFD simulations based on the ALE Navier-Stokes equations together with radial basis function mesh interpolation are used. For the 'clap-and-peel' motion an immersed symmetry plane is introduced...
conference paper 2011
document
Loeven, G.J.A. (author), Bijl, H. (author)
Due to manufacturing tolerances, the airfoil of a wing after production is never exactly the same as the designed airfoil. Also during operation the geometry may change due to aerodynamic loading, icing or wear of the construction. The geometry can, therefore, be treated as uncertain. Uncertainties in the geometry of an airfoil are expected to...
conference paper 2008
document
Bijl, H. (author), Van Zuijlen, A.H. (author), Bosscher, S. (author)
In this paper we use the multigrid algorithm - commonly used to improve the efficiency of the flow solver - to improve the efficiency of partitioned fluid-structure interaction iterations. Coupling not only the structure with the fine flow mesh, but also with the coarse flow mesh (often present due to the multigrid scheme) leads to a significant...
conference paper 2006
document
Blom, D.S. (author), Krupp, V. (author), Van Zuijlen, A.H. (author), Klimach, H. (author), Roller, S. (author), Bijl, H. (author)
Multi-physics simulations, such as fluid-structure-acoustics interaction (FSA), require a high performance computing environment in order to perform the simulation in a reasonable amount of computation time. Currently used coupling methods use a staggered execution of the fluid and solid solver [6], which leads to inherent load imbalances. In ...
conference paper 2015
document
Gillebaart, T. (author), Van Zuijlen, A.H. (author), Bijl, H. (author)
In this paper, the influence of wing flexibility and the 'clap-and-peel' motion (one versus two wings) on the upward (lifting) force in hover is studied. CFD simulations based on the ALE Navier-Stokes equations together with radial basis function mesh interpolation are used. For the 'clap-and-peel' motion an immersed symmetry plane is introduced...
conference paper 2011
document
Bijl, H. (author), Van Zuijlen, A.H. (author), Bosscher, S. (author)
In this paper we use the multigrid algorithm - commonly used to improve the efficiency of the flow solver - to improve the efficiency of partitioned fluid-structure interaction iterations. Coupling not only the structure with the fine flow mesh, but also with the coarse flow mesh (often present due to the multigrid scheme) leads to a significant...
conference paper 2006
document
Tay, W.B. (author), Van Oudheusden, B.W. (author), Bijl, H. (author)
The numerical simulation of a “X-wing” type biplane flapping wings, has been performed in 3D using the Immersed Boundary Method (IBM). This “X-wing” type flapping configuration draws its inspiration from Delfly [1], a family of ornithopters developed by the Delft University of Technology, as shown in Figure 1. The unique “X-wing” design features...
conference paper 2013
document
De Boer, A. (author), Van der Schoot, M.S. (author), Bijl, H. (author)
A new point-by-point mesh movement algorithm is developed for the deformation of unstructured grids. The method is based on using radial basis function, RBFs, to interpolate the displacements of the boundary nodes to the whole flow mesh. A small system of equations has to be solved, only involving the nodes on the boundary of the flow domain....
conference paper 2006
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