References of "Terrapon, Vincent"
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See detailNumerical and experimental study of the flow around a 4:1 rectangular cylinder at moderate Reynolds number
Guissart, Amandine ULiege; Andrianne, Thomas ULiege; Dimitriadis, Grigorios ULiege et al

in Journal of Wind Engineering and Industrial Aerodynamics (2019), 189

This paper presents the results of investigations into the flow around a rectangular cylinder with a chord-to-depth ratio equal to 4. The studies are performed through wind tunnel dynamic pressure ... [more ▼]

This paper presents the results of investigations into the flow around a rectangular cylinder with a chord-to-depth ratio equal to 4. The studies are performed through wind tunnel dynamic pressure measurements along a cross section combined with two-dimensional Unsteady Reynolds-Averaged Navier-Stokes (URANS) and three-dimensional Delayed-Detached Eddy Simulation (DDES). These experimental and numerical studies are complementary and combining them allows a better understanding of the unsteady dynamics of the flow. These studies aim mainly at determining the effects of the rectangle incidence and freestream velocity on the variation of the flow topology and the aerodynamic loads, and at assessing the capability of the industrially affordable URANS and DDES approaches to provide a sufficiently accurate estimation of the flow for different incidences. The comparison of experimental and numerical data is performed using statistics and Dynamic Mode Decomposition. It is shown that the rectangular cylinder involves complex separation-reattachment phenomena that are highly sensitive to the Reynolds number. In particular, the time-averaged lift slope increases rapidly with the Reynolds number in the range 7.8e3 < Re < 1.9e4 due to the modification of the time-averaged vortex strength, thickness and distance from the surface. Additionally, it is shown that both URANS and DDES simulations fail to accurately predict the flow at all the different incidence angles considered. The URANS approach is able to qualitatively estimate the spatio-temporal variations of vortices for incidences below the stall angle alpha = 4°. Nonetheless, URANS does not predict stall, while DDES correctly identifies the stall angle observed experimentally. [less ▲]

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See detailComputation of Leishman-Beddoes model parameters using unsteady RANS simulations
Sanchez Martinez, Mariano ULiege; Boutet, Johan ULiege; Amandolese, Xavier et al

in Proceedings of the AIAA SciTech 2019 Forum and Exhibition (2019, January)

The determination of the Leishman-Beddoes (LB) model parameter values from experimental measurements and Computational Fluid Dynamic (CFD) simulations is presented. Two-dimensional unsteady RANS ... [more ▼]

The determination of the Leishman-Beddoes (LB) model parameter values from experimental measurements and Computational Fluid Dynamic (CFD) simulations is presented. Two-dimensional unsteady RANS simulations are carried out for experimental test cases of two airfoils oscillating in pitch in the wind tunnel at Reynolds numbers of the order of Re=1.8e4. The RANS results are first compared directly to the experimental measurements and it is shown that the simulations cannot represent some important aspects of the physics of the phenomenon, such as the effect of a laminar separation bubble occurring at low angles of attack and the effect of the resulting leading edge vortex once it has started travelling over the surface of the airfoil. The flowfields computed from the CFD simulations are then used to estimate the values of three parameters for the Leishman-Beddoes model. The aim is to explore the possibility of using the LB model as a reduced order model for CFD simulations. It is shown that the inaccuracies of the CFD simulations lead to inaccurate parameter values, such as an overestimation of the leading edge vortex shedding time. Nevertheless, the resulting LB model can smooth the oscillations in the post-stall load responses predicted by the CFD. It is concluded that higher-fidelity simulations are necessary, involving a boundary transition model or even Large Eddy Simulation schemes. [less ▲]

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See detailUnsteady aerodynamic modeling methodology based on dynamic mode interpolation for transonic flutter calculations
Güner, Hüseyin ULiege; Thomas, David ULiege; Dimitriadis, Grigorios ULiege et al

in Journal of Fluids and Structures (2019), 84

A new unsteady aerodynamic modeling methodology for calculating transonic flutter characteristics is presented. The main idea of the methodology is to obtain the unsteady flow response to small amplitude ... [more ▼]

A new unsteady aerodynamic modeling methodology for calculating transonic flutter characteristics is presented. The main idea of the methodology is to obtain the unsteady flow response to small amplitude periodic deformations of a structure over a large range of oscillation frequencies through the interpolation of the most dominant fluid dynamic modes obtained from Dynamic Mode Decomposition (DMD) of a few reference unsteady simulations at different oscillation frequencies. These simulations can be carried out by solving the Euler or RANS equations. The methodology can then be used to obtain a frequency-domain generalized aerodynamic force matrix, and stability analysis can be performed using standard flutter analysis methods such as the p-k method. The proposed methodology provides a very good estimate of the flutter boundary for the 2D Isogai airfoil and 3D AGARD 445.6 wing models, but at a lower computational cost than the traditional higher-fidelity Fluid-Structure Interaction (FSI) simulations. [less ▲]

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See detailCUPyDO - An integrated Python environment for coupled fluid-structure simulations
Thomas, David ULiege; Cerquaglia, Marco Lucio ULiege; Boman, Romain ULiege et al

in Advances in Engineering Software (2019)

CUPyDO, a fluid-structure interaction (FSI) tool that couples existing independent fluid and solid solvers into a single synchronization and communication framework based on the Python language is ... [more ▼]

CUPyDO, a fluid-structure interaction (FSI) tool that couples existing independent fluid and solid solvers into a single synchronization and communication framework based on the Python language is presented. Each coupled solver has to be wrapped in a Python layer in order to embed their functionalities (usually written in a compiled language) into a Python object, that is called and used by the coupler. Thus a staggered strong coupling can be achieved for time-dependent FSI problems such as aeroelastic flutter, vortex-induced vibrations (VIV) or conjugate heat transfer (CHT). The synchronization between the solvers is performed with the predictive block-Gauss-Seidel algorithm with dynamic under-relaxation. The tool is capable of treating non-matching meshes between the fluid and structure domains and is optimized to work in parallel using Message Passing Interface (MPI). The implementation of CUPyDO is described and its capabilities are demonstrated on typical validation cases. The open-source code SU2 is used to solve the fluid equations while the solid equations are solved either by a simple rigid body integrator or by in-house linear/nonlinear Finite Element codes (GetDP/Metafor). First, the modularity of the coupling as well as its ease of use is highlighted and then the accuracy of the results is demonstrated. [less ▲]

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See detailHigher Fidelity Transonic Aerodynamic Modeling in Preliminary Aircraft Design
Crovato, Adrien ULiege; Dimitriadis, Grigorios ULiege; Terrapon, Vincent ULiege

in Proceedings of the 31st Congress of the International Council of the Aeronautical Sciences (2018, September 11)

There is a consensus in the aerospace research community that future aircraft will be more flex- ible and their wings will be more highly loaded. While this development is likely to increase air- craft ... [more ▼]

There is a consensus in the aerospace research community that future aircraft will be more flex- ible and their wings will be more highly loaded. While this development is likely to increase air- craft efficiency, it poses several aeroelastic ques- tions. Current aeroelastic tailoring practice for early preliminary aircraft design relies on linear aerodynamic modeling, which is unable to pre- dict shocks and boundary layers. The objective of this research is to enhance the linear aerodynamic modeling methodology, thus allowing fast and re- liable aerodynamic loads prediction for aeroelas- tic computations. First, the different levels of fi- delity of aerodynamic modeling that can be used in aircraft design are reviewed and compared on benchmark test cases. A Field Panel Method is subsequently developed and implemented. Pre- liminary results are presented and possible future enhancements are detailed. [less ▲]

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See detailInviscid and viscous flow modeling for fast transonic flutter calculations
Güner, Hüseyin ULiege; Dimitriadis, Grigorios ULiege; Terrapon, Vincent ULiege

in Proceedings of the International Council of Aeronautical Sciences, ICAS 2018 (2018, September 10)

Transonic aeroelastic analysis at the design level relies on linear panel methods, such as the Doublet Lattice approach, usually after application of transonic corrections. The results from these ... [more ▼]

Transonic aeroelastic analysis at the design level relies on linear panel methods, such as the Doublet Lattice approach, usually after application of transonic corrections. The results from these calculations cannot predict shock motion, shock-boundary layer interactions and the effects of such phenomena on flutter behavior, even after corrections are applied, since the latter are generally quasi-steady. This paper proposes a higher-fidelity approach that involves the solutions of the flow equations in order to obtain the unsteady flow response to relatively small amplitude periodic deformations of a structure over a large range of oscillation frequencies. The main idea is to perform a few high-fidelity CFD simulations, such as Euler or RANS simulations, with an imposed structural deformation at selected oscillation frequencies so as to capture the most dominant nonlinear dynamic modes of the flow response. These fluid dynamic modes are then interpolated to estimate the flow response for any other oscillation frequency. The methodology can then be used to obtain a frequency-domain generalized aerodynamic force matrix, and stability analysis can be performed using standard flutter calculation methods such as the p-k method. The present methodology provides a very good estimate of the flutter boundary for the 2D Isogai airfoil validation case, but at much lower computational cost than the traditional higher-fidelity Fluid-Structure Interaction (FSI) simulations. [less ▲]

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See detailSteady Transonic Aerodynamic Modeling for Aeroelastic Computations
Crovato, Adrien ULiege; Dimitriadis, Grigorios ULiege; Terrapon, Vincent ULiege

Scientific conference (2018, July 04)

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See detailTwo-dimensional dynamics of elasto-inertial turbulence and its role in polymer drag reduction
Sid, Samir ULiege; Dubief, Yves; Terrapon, Vincent ULiege

in Physical Review Fluids (2018), 3(1),

Direct numerical simulations of a FENE-P fluid in both two- and three-dimensional straight periodic channels find that elasto-inertial turbulence is fundementally two-dimensional. The spurious effect of ... [more ▼]

Direct numerical simulations of a FENE-P fluid in both two- and three-dimensional straight periodic channels find that elasto-inertial turbulence is fundementally two-dimensional. The spurious effect of artificial diffusion of the polymer is demonstrated. [less ▲]

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See detailRole of Elasto-Inertial Turbulence in Polymer Drag Reduction
Dubief, Yves; Sid, Samir ULiege; Terrapon, Vincent ULiege

Conference (2017, November 20)

Elasto-Inertial Turbulence (EIT) is a peculiar state of turbulence found in dilute polymer solutions flowing in parallel wall flows over a wide range of Reynolds numbers. At subcritical Reynolds numbers ... [more ▼]

Elasto-Inertial Turbulence (EIT) is a peculiar state of turbulence found in dilute polymer solutions flowing in parallel wall flows over a wide range of Reynolds numbers. At subcritical Reynolds numbers, appropriate boundary conditions trigger EIT, a self-sustaining cycle of energy transfers between thin sheets of stretched polymers and velocity perturbations, which translates into an increase of friction drag. For critical and supercritical Reynolds numbers, polymer additives may lead to significant drag reduction, bounded by the asymptotic state known as Maximum Drag Reduction (MDR). The present research investigates the role of EIT in the dynamics of critical and supercritical Reynolds number wall flows. Using high-fidelity direct numerical simulations of channel flows and the FENE-P model, we establish that (i) EIT is two-dimensional, (ii) the scales essential to the existence of EIT are sub-Kolmogorov, and (iii) EIT drives MDR at low and possibly moderate Reynolds number turbulent flows. These findings were validated in two different codes and using unprecedented resolutions for polymer flows. [less ▲]

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See detailThe role of elasto-inertial turbulence on channel flow drag
Terrapon, Vincent ULiege; Sid, Samir ULiege; Dubief, Yves

Conference (2017, August 24)

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See detailOn the interactions between mean shear and natural convection in turbulent mixed convection
Sid, Samir ULiege; Dubief, Yves; Terrapon, Vincent ULiege

Conference (2017, August 24)

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See detailTransonic aerodynamic modeling & new FSI infrastructure
Terrapon, Vincent ULiege; Dimitriadis, Grigorios ULiege; Crovato, Adrien ULiege et al

Scientific conference (2017, August 10)

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See detailUnsteady pressure distributions on a 4:1 rectangular cylinder: comparison of numerical and experimental results using decomposition methods.
Guissart, Amandine ULiege; Andrianne, Thomas ULiege; Dimitriadis, Grigorios ULiege et al

Conference (2017, July 04)

Detached flows around bluff bodies are ubiquitous in civil engineering applications. In this work, the flow around a static 4:1 rectangular cylinder at moderate Reynolds number and at different angles of ... [more ▼]

Detached flows around bluff bodies are ubiquitous in civil engineering applications. In this work, the flow around a static 4:1 rectangular cylinder at moderate Reynolds number and at different angles of incidence is studied using both Experimental Fluid Dynamics (EFD) and Computational Fluid Dynamics (CFD). Typically, the integration of EFD and CFD allows a better understanding of the flow of interest by leveraging the complementary of their respective outputs. However, the comparison of computational and experimental results is an important but difficult step of this integration, particularly in the case of local quantities related to unsteady flows. In this work, decomposition methods are used to compare unsteady loads and pressure distributions coming from EFD and CFD. In particular, Proper Orthogonal Decomposition (POD) and Dynamic Mode Decomposition (DMD) are used to extract the dominant structures of the aerodynamic coefficients. The experimental data are obtained from dynamic pressure measurements in wind tunnel while numerical data come from two-dimensional unsteady Reynolds-Averaged Navier-Stokes (uRANS) simulations and tri-dimensional Delayed-Detached Eddy Simulations (DDES). This work shows that the decomposition methods represent a powerful tool enabling the analysis and the quantitative comparison of the main spatial and temporal characteristics of unsteady flows. Moreover, the accuracy of uRANS and DDES results is analyzed in light of the capacity of both CFD techniques to capture the reattachment occurring on the upper part of the rectangular cylinder. [less ▲]

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See detailResearch on Fast Aeroelastic Modeling Methods for the Transonic Regime
Güner, Hüseyin ULiege; Dimitriadis, Grigorios ULiege; Terrapon, Vincent ULiege

in Proceedings of the International Forum on Aeroelasticity and Structural Dynamics, IFASD 2017 (2017, June 27)

Two methods for modeling unsteady transonic flows at low computational cost are presented as a first step towards a fast and accurate aeroelastic calculation methodology for the preliminary design stage ... [more ▼]

Two methods for modeling unsteady transonic flows at low computational cost are presented as a first step towards a fast and accurate aeroelastic calculation methodology for the preliminary design stage in the transonic flow regime. The first approach corresponds to a quasi-steady approximation based on few steady simulations that is improved through the use of an unsteady filter. The second approach is based on the interpolation of dynamic modes between solutions at different frequencies that are obtained either from Dynamic Mode Decomposition (DMD) of unsteady simulations or directly from Harmonic Balance (HB) simulations. The two methods are illustrated in the case of a pitching airfoil in the transonic regime. Results show that the first method is fast and provides a first approximation of the unsteady dynamics. The computational cost of the second approach is higher, but the method provides better results in predicting aerodynamic forces and shock motion for a large range of reduced frequencies. [less ▲]

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See detailStaggered strong coupling between existing fluid and solid solvers through a Python interface for fluid-structure interaction problems
Thomas, David ULiege; Variyar, Anil; Boman, Romain ULiege et al

in Proceedings of the VII International Conference on Coupled Problems in Science and Engineering (2017, June)

Detailed reference viewed: 82 (22 ULiège)