The Experts below are selected from a list of 315 Experts worldwide ranked by ideXlab platform
Zafer Gürdal - One of the best experts on this subject based on the ideXlab platform.
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Aeroelastic tailoring using lamination parameters
Structural and Multidisciplinary Optimization, 2010Co-Authors: Glenn A. A. Thuwis, Mostafa M. Abdalla, Roeland De Breuker, Zafer GürdalAbstract:The aim of the present work is to passively reduce the induced drag of the rear wing of a Formula One car at high velocity through aeroelastic tailoring. The angle-of-attack of the rear wing is fixed and is determined by the required downforce needed to get around a turn. As a result, at higher velocity, the amount of downforce and related induced drag increases. The maximum speed on a straight part is thus reduced due to the increase in induced drag. A fibre reinforced composite torsion box with extension-shear coupled upper and lower skins is used leading to bending-torsion coupling. Three-dimensional static aeroelastic analysis is performed loosely coupling the Finite Element Code Nastran and the Computational Fluid Dynamics Panel Code VSAERO using ModelCenter. A wing representative of Formula One rear wings is optimised for minimum induced drag using a response surface methodology. Results indicate that a substantial induced drag reduction is achievable while maintaining the desired downforce during low speed turns.
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Aeroelastic tailoring using lamination parameters : Drag reduction of a Formula One rear wing
Structural and Multidisciplinary Optimization, 2009Co-Authors: Glenn A. A. Thuwis, Mostafa Abdalla, Roeland De Breuker, Zafer GürdalAbstract:The aim of the present work is to passively reduce the induced drag of the rear wing of a Formula One car at high velocity through aeroelastic tailoring. The angle-of-attack of the rear wing is fixed and is determined by the required downforce needed to get around a turn. As a result, at higher velocity, the amount of downforce and related induced drag increases. The maximum speed on a straight part is thus reduced due to the increase in induced drag. A fibre reinforced composite torsion box with extension-shear coupled upper and lower skins is used leading to bending-torsion coupling. Three-dimensional static aeroelastic analysis is performed loosely coupling the Finite Element Code Nastran and the Computational Fluid Dynamics Panel Code VSAERO using ModelCenter. A wing representative of Formula One rear wings is optimised for minimum induced drag using a response surface methodology. Results indicate that a substantial induced drag reduction is achievable while maintaining the desired downforce during low speed turns.
Urpo Pesonen - One of the best experts on this subject based on the ideXlab platform.
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an object oriented re engineering of a three dimensional higher order subsonic supersonic Panel Code hisss
16th AIAA Computational Fluid Dynamics Conference, 2003Co-Authors: K Pushparaj, Ramesh K Agarwal, Urpo PesonenAbstract:An existing Fortran Code HISSS is reengineered into an object-oriented Code using Java. HISSS is a three-dimensional Panel method Code, which computes the inviscid flow past arbitrary wing-body configurations at subsonic and supersonic speed using a higher-order singularity method. In HISSS, surface of the configuration and its wake are modeled by networks of Panels that carry singularity distributions on them. Sources are used to represent the thickness of the configuration, and doublets represent the circulation and the generated lift. The strengths of these singularities are determined by imposing appropriate boundary conditions on a set of control points. The re-engineered Java Code is embedded with object-oriented programming language features like
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An Object-Oriented Re-Engineering of a Three-Dimensional Higher-Order Subsonic/Supersonic Panel Code -HISSS
16th AIAA Computational Fluid Dynamics Conference, 2003Co-Authors: K Pushparaj, Ramesh K Agarwal, Urpo PesonenAbstract:An existing Fortran Code HISSS is reengineered into an object-oriented Code using Java. HISSS is a three-dimensional Panel method Code, which computes the inviscid flow past arbitrary wing-body configurations at subsonic and supersonic speed using a higher-order singularity method. In HISSS, surface of the configuration and its wake are modeled by networks of Panels that carry singularity distributions on them. Sources are used to represent the thickness of the configuration, and doublets represent the circulation and the generated lift. The strengths of these singularities are determined by imposing appropriate boundary conditions on a set of control points. The re-engineered Java Code is embedded with object-oriented programming language features like
Pepijn De Jong - One of the best experts on this subject based on the ideXlab platform.
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deterministic validation of a time domain Panel Code for parametric roll
2019Co-Authors: Frans Van Walree, Pepijn De JongAbstract:Validation of simulation methods for dynamic stability is hampered by the fact that dynamic stability phenomena can be quite rare. In order to obtain sufficient statistical confidence in both experimental data and simulation results long duration time histories are required for a range of operational conditions. This is at most times not feasible from a practical point of view. One way of validating time domain simulation methods for dynamic stability phenomena is by deterministic validation. This means that the simulation is run in the same wave sequence as used during the model experiments. Ideally, a one to one comparison between experiments and simulations is then possible. A difficulty in such an approach is, in case of irregular waves, the reconstruction of the experimental wave train in the simulation tool. Even if this were successful, the encountered wave train in the simulations will deviate from the experimental one because it is inevitable that the position in the horizontal plane will differ from the experimental one after some time. The paper describes the deterministic validation of a non-linear, 6-DoF time domain Panel Code for parametric roll. The paper explains the method for reconstructing the experimental wave train in the simulation method and how to circumvent the problem of the deviation in horizontal position. Finally, comparisons between experimental and simulated time traces are given for the motions in the vertical plane.
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validation of a time domain Panel Code for high speed craft operating in stern quartering seas
2011Co-Authors: Frans Van Walree, Pepijn De JongAbstract:The paper describes the validation of a time domain method to simulate the behaviour of a fast patrol boat operating in stern-quartering seas. First, the simulation method is described. Subsequently results of validation based on motion statistics are presented, showing that the statistical uncertainty in predicting horizontal plane motions is large. Finally, to overcome this, a method is described to reconstruct experimental wave trains and the results of deterministic validation are presented showing satisfactory agreement between computed and measured time traces. Results suggest that the method can be used to investigate dynamic stability and course keeping in stern quartering seas.
Glenn A. A. Thuwis - One of the best experts on this subject based on the ideXlab platform.
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Aeroelastic tailoring using lamination parameters
Structural and Multidisciplinary Optimization, 2010Co-Authors: Glenn A. A. Thuwis, Mostafa M. Abdalla, Roeland De Breuker, Zafer GürdalAbstract:The aim of the present work is to passively reduce the induced drag of the rear wing of a Formula One car at high velocity through aeroelastic tailoring. The angle-of-attack of the rear wing is fixed and is determined by the required downforce needed to get around a turn. As a result, at higher velocity, the amount of downforce and related induced drag increases. The maximum speed on a straight part is thus reduced due to the increase in induced drag. A fibre reinforced composite torsion box with extension-shear coupled upper and lower skins is used leading to bending-torsion coupling. Three-dimensional static aeroelastic analysis is performed loosely coupling the Finite Element Code Nastran and the Computational Fluid Dynamics Panel Code VSAERO using ModelCenter. A wing representative of Formula One rear wings is optimised for minimum induced drag using a response surface methodology. Results indicate that a substantial induced drag reduction is achievable while maintaining the desired downforce during low speed turns.
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Aeroelastic tailoring using lamination parameters : Drag reduction of a Formula One rear wing
Structural and Multidisciplinary Optimization, 2009Co-Authors: Glenn A. A. Thuwis, Mostafa Abdalla, Roeland De Breuker, Zafer GürdalAbstract:The aim of the present work is to passively reduce the induced drag of the rear wing of a Formula One car at high velocity through aeroelastic tailoring. The angle-of-attack of the rear wing is fixed and is determined by the required downforce needed to get around a turn. As a result, at higher velocity, the amount of downforce and related induced drag increases. The maximum speed on a straight part is thus reduced due to the increase in induced drag. A fibre reinforced composite torsion box with extension-shear coupled upper and lower skins is used leading to bending-torsion coupling. Three-dimensional static aeroelastic analysis is performed loosely coupling the Finite Element Code Nastran and the Computational Fluid Dynamics Panel Code VSAERO using ModelCenter. A wing representative of Formula One rear wings is optimised for minimum induced drag using a response surface methodology. Results indicate that a substantial induced drag reduction is achievable while maintaining the desired downforce during low speed turns.
Daniele Ragni - One of the best experts on this subject based on the ideXlab platform.
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a fast Panel Code for complex actuator disk flows
55th AIAA Aerospace Sciences Meeting, 2017Co-Authors: Simon Gamme, Gael De Oliveira, Daniele RagniAbstract:A fast, linear scaling vortex method is presented to study inviscid incompressible flow problems involving one or more actuator disks. Building upon previous efforts that were limited to axi-symmetric flow cases, the proposed methodology is able to handle arbitrary configurations with no symmetry constraints. Applications include the conceptual study of wake interaction mechanisms in wind farms, and the correction of wind tunnel blockage effects in test sections of arbitrary shape. Actuator disks represent wind turbines through the shedding of a deformable vortex wake, discretized with a plaid of triangular distributed dipole singularities. An iterative method is adopted to align the wake with the local flow field, which is reconstructed from the vorticity field with a Green function approach. Interactions are computed with a Fast Multipole Method (FMM), effectively overcoming the quadratic scaling of computational time associated with traditional Panel methods. When compared to direct computation, the use of an FMM algorithm reduced solution time by a factor 30 when studying the wake of a single actuator disk with 60000 Panels. In the same case, the mass flux of the actuator streamtube was conserved to 0:002%. Finally, the presence of round and square impermeable walls around the actuator is considered to demonstrate the Code applicability to wind tunnel wall interference correction problems.
