Jordi Pons Prats Profile : Scipedia

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Jordi Pons-Prats' publications

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This is the collection of the publications of Jordi Pons-Prats, researcher and leader of the Aerospace Engineering group at CIMNE.

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CM3-2017 - Computation and Big Data in Transport

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In the upcoming decade the integration of Advanced Multidisciplinary Simulation (MS), Optimization (MO) and Big Data Analysis (MBDA) tools will have a major impact on systemic procedures in both industrial and societal environments linked to Smart, Green and Integrated Transport [...]

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Presentations to the Open Workshop PADRI2017 - Platform for Aircraft Drag Reduction Innovation

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About PADRI-2017

The main objective of the Open Workshop PADRI2017 (http://congress.cimne.com/padri-2017/frontal/default.asp) is to find candidate flow control technologies and optimization strategies that can minimize shock wave and interference drag in the strut-wing junction region in cruise condition.

The ECCOMAS Industry Interest Group (IIG) is actively promoting the ECCOMAS Advanced Workshop PADRI.
The high level objective of this workshop is to strengthen the ECCOMAS industrial group and to develop contact between ECCOMAS and the DGs of the European Commission.

PADRI2017 proposes a test case reproducing, even at low velocity, a typical shock wave pattern in the region of the junction strut-wing of an aircraft. In order to simplify the problem, some constraints have been setup, so that the geometrical modifications should be confined to a defined small region around the strut-wing junction, and the objective function is clearly explained in order to ensure computational data results comparisons across all the technology solutions and participants.
A computational platform will allow all participants to compare on outputs and formats selected by organizers their respective data results installed on a Database with respect to the reference (baseline) and to show the benefit of the chosen flow control technology.

The workshop intends to contribute to fill the gap between the different technology models and their application.

Technical Description of the Test Case

Strut wing test case is based on an unformatted geometry of an aircraft with upper wing, which is supported by a strut. The geometry includes the entire aircraft with tail and empennage, but simplifications can be applied if necessary, discarding the empennage and tail, or considering symmetry.
The flow conditions are summarized as: Mach 0.72, angle of attack 1º, Reynolds number over length 7.1x106 m-1, cruise altitude 30000ft on an atmosphere ISA+0 with pressure 30089.59 Pa, and temperature 228.71K.

Mach= 0.72
Angle of attack= 1°
Reynolds/length= 7.1.106m1
Altitude= 30000 ft
Atmosphere= ISA+0
Pressure= 30089.59 Pa
Temperature= 228.71 K

The main focus should be put on the region of the strut-wing junction in the mentioned cruise conditions, analyzing the shock wave and the interference drag in this particular region.
The definition of the best flow control device, which helps to diminish the shock and the drag, is the main objective and should be demonstrated through the analysis of the simulation results.

Conference organized by CIMNE Congress Bureau.

Scope

About PADRI-2017

The main objective of the Open Workshop PADRI2017 (http://congress.cimne.com/padri-2017/frontal/default.asp) is to find candidate flow control technologies and optimization [...]

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Documents published in Scipedia

Industrial application of genetic algorithms to cost reduction of a wind turbine equipped with a tuned mass damper
J. Pons Prats, M. Coma, J. Betran, X. Roca, G. Bugeda

(2018). Andrés-Pérez E., González L., Periaux J., Gauger N., Quagliarella D., Giannakoglou K. (eds) Evolutionary and Deterministic Methods for Design Optimization and Control With Applications to Industrial and Societal Problems. Computational Methods in Applied Sciences, vol 49. Springer, Cham

Abstract
Design optimization has already become an important tool in industry. The benefits are clear, but several drawbacks are still present, being the main one the computational cost. The numerical simulation involved in the solution of each evaluation is usually costly, but time and computational resources are limited. Time is key in industry. The present communication focuses on the methodology applied to optimize the installation and design of a Tuned Mass Damper. It is a structural device installed within the tower of a wind turbine aimed to stabilize the oscillations and reduce the tensions and the fatigue loads. The paper describes the decision process to define the optimization problem, as well as the issues and solutions applied to deal with a huge computational cost.
Abstract
Design optimization has already become an important tool in industry. The benefits are clear, but several drawbacks are still present, being the main one the computational [...]
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Description of the Test Cases
G. Bugeda, J. Periaux, N. Qin, J. Pons Prats

(2020). Qin N., Periaux J., Bugeda G. (eds) Advances in Effective Flow Separation Control for Aircraft Drag Reduction. Computational Methods in Applied Sciences, vol 52. Springer, Cham

Abstract
The high-level objective of MARS project was to understand the formation and behaviour of turbulent structures which affects the Reynolds stress and skin friction. The aim was, once understood, to apply flow control techniques in order to control these structures and reduce the overall drag derived from the Reynolds stress and mainly from the skin friction. Active flow control devices were the main interest; DBD plasma, Synthetic jets, Micro Blowing and Suction, Moving Surfaces were included on the list. To test all these devices, two test cases were defined, and a database and file repository were established in the project webserver. The present chapter is aimed to describe the test cases, including the set-up of the flow control devices, as well as to describe the file repository were all the data was stored.
Abstract
The high-level objective of MARS project was to understand the formation and behaviour of turbulent structures which affects the Reynolds stress and skin friction. The aim [...]
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Optimization of the Experimental Set-up for a Turbulent Separated Shear Flow Control by Plasma Actuator Using Genetic Algorithms
N. Benard, J. Pons Prats, J. Periaux, J. Bonnet, G. Bugeda

(2020). Qin N., Periaux J., Bugeda G. (eds) Advances in Effective Flow Separation Control for Aircraft Drag Reduction. Computational Methods in Applied Sciences, vol 52. Springer, Cham

Abstract
Since 1947, when Schubauer and Skramstad established the basis of the technology with its revolutionary work about steady state tools and mechanisms for the flow management, the progress of the flow control technology and the development of devices have progressed constantly. Anyway, the applicability of such devices is limited, and only few of them have arrived to the assembly workshop. The problem is that the range of actuation is still limited. Despite their operability limitations, flow control devices are of great interest for the aeronautical industry. The number of projects investigating this technology demonstrates the relevance of in the Fluid Dynamic field. The scientific interest focus not only on the industrial applications and the improvement of the technology, but also on the deep understanding of the physical phenomena associated to the flow separation, turbulence formation associated to the final drag reduction aim. A clear example of what has been mentioned is the EC MARS research project (MARS project, FP7 project number 266326, [2]). Its objectives are aimed to a better understanding of the Reynolds Stress and turbulent flow related to both drag reduction and flow control. The research was carried out through the analysis of several flow control devices and the optimization of the parameters for some of them was an important element of the research. When solving a traditional fluid dynamics optimisation problem numerical flow analysis are used instead of experimental ones due to their lower cost and shorter needed time for evaluation of candidate solutions. Nevertheless, in the particular case of the selected flow control plasma devices the experimental measurement of the performance of each candidate configuration has been much quicker than a numerical analysis. For this reason, the corresponding optimisation problem has been solved by coupling an evolutionary optimization algorithm with an experimental device. This paper discusses the design quality and efficiency gained by this innovative coupling.
Abstract
Since 1947, when Schubauer and Skramstad established the basis of the technology with its revolutionary work about steady state tools and mechanisms for the flow management, [...]
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Drag reduction via turbulent boundary layer flow control
A. Abbas, G. Bugeda, E. Ferrer, S. Fu, J. Periaux, J. Pons Prats, E. Valero, Y. Zheng

Science China-Technological Sciences (2017). Vol. 60 (9), pp. 1281-1290 (Preprint)

Abstract
Turbulent boundary layer control (TBLC) for skin-friction drag reduction is a relatively new technology made possible through the advances in computational-simulation capabilities, which have improved the understanding of the flow structures of turbulence. Advances in micro-electronic technology have enabled the fabrication of active device systems able to manipulating these structures. The combination of simulation, understanding and micro-actuation technologies offers new opportunities to significantly decrease drag, and by doing so, to increase fuel efficiency of future aircraft. The literature review that follows shows that the application of active control turbulent skin-friction drag reduction is considered of prime importance by industry, even though it is still at a low technology readiness level (TRL). This review presents the state of the art of different technologies oriented to the active and passive control for turbulent skin-friction drag reduction and contributes to the improvement of these technologies.
Abstract
Turbulent boundary layer control (TBLC) for skin-friction drag reduction is a relatively new technology made possible through the advances in computational-simulation capabilities, [...]
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Turbulent separated shear flow control by surface plasma actuator: experimental optimization by genetic algorithm approach
N. Benard, J. Pons Prats, J. Periaux, G. Bugeda, P. Braud, J. Bonnet, E. Moreau

Experiments in Fluids (2016). (preprint) Vol. 57 (2), pp. 1-17

Abstract
The potential benefits of active flow control are no more debated. Among many others applications, flow control provides an effective mean for manipulating turbulent separated flows. Here, a nonthermal surface plasma discharge (dielectric barrier discharge) is installed at the step corner of a backward-facing step (U 0 = 15 m/s, Re h = 30,000, Re θ = 1650). Wall pressure sensors are used to estimate the reattaching location downstream of the step (objective function #1) and also to measure the wall pressure fluctuation coefficients (objective function #2). An autonomous multi-variable optimization by genetic algorithm is implemented in an experiment for optimizing simultaneously the voltage amplitude, the burst frequency and the duty cycle of the high-voltage signal producing the surface plasma discharge. The single-objective optimization problems concern alternatively the minimization of the objective function #1 and the maximization of the objective function #2. The present paper demonstrates that when coupled with the plasma actuator and the wall pressure sensors, the genetic algorithm can find the optimum forcing conditions in only a few generations. At the end of the iterative search process, the minimum reattaching position is achieved by forcing the flow at the shear layer mode where a large spreading rate is obtained by increasing the periodicity of the vortex street and by enhancing the vortex pairing process. The objective function #2 is maximized for an actuation at half the shear layer mode. In this specific forcing mode, time-resolved PIV shows that the vortex pairing is reduced and that the strong fluctuations of the wall pressure coefficients result from the periodic passages of flow structures whose size corresponds to the height of the step model.
Abstract
The potential benefits of active flow control are no more debated. Among many others applications, flow control provides an effective mean for manipulating turbulent separated [...]
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Applying multi-objective robust design optimization procedure to the route planning of a commercial aircraft
J. Pons Prats, G. Bugeda, F. Zarate, E. Oñate, J. Periaux

(2018). Computational Methods and Models for Transport. Computational Methods in Applied Sciences. Diez, P. Neittaanmäki, P., Periaux, J., Tuovinen, T., Bräysy, O. (Eds.), Vol. 45, pp. 147-167, Springer, Cham

Abstract
Aircraft emission targets worldwide and their climatic effects have put pressure in government agencies, aircraft manufacturers and airlines to reduce water vapour, carbon dioxide (CO2CO2) and oxides of nitrogen (NOxNOx) resulting from aircraft emissions. The difficulty of reducing emissions including water vapor, carbon dioxide (CO2CO2) and oxides of nitrogen (NOxNOx) is mainly due to the fact that a commercial aircraft is usually designed for a particular optimal cruise altitude but may be requested or required to operate and deviate at different altitudes and speeds to archive a desired or commanded flight plan, resulting in increased emissions. This is a multi- disciplinary problem with multiple trade-offs such as optimizing engine efficiency, minimizing fuel burnt and emissions while maintaining prescribed aircraft trajectories, altitude profiles and air safety. There are possible attempts to solve such problems by designing new wing/aircraft shape, new efficient engine, ATM technology, or modifying the aircraft flight plan. Based on the rough data provided by an air carrier company, who was willing to assess the methodology, this paper will present the coupling of an advanced optimization technique with mathematical models and algorithms for aircraft emission, and fuel burnt reduction through flight plan optimization. Two different approaches are presented; the first one describes a deterministic optimization of the flight plan and altitude profile in order to reduce the fuel consumption while reducing time and distance. The second approach presents the robust design optimization of the previous case considering uncertainties on several parameters. Numerical results will show that the methods are able to capture a set of useful trade-offs solutions between aircraft range and fuel consumption, as well as fuel consumption and flight time.
Abstract
Aircraft emission targets worldwide and their climatic effects have put pressure in government agencies, aircraft manufacturers and airlines to reduce water vapour, carbon [...]
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Study of the aerodynamic forces on a simplified shape X-43 aircraft under supersonic conditions, design optimization
L. Caros, C. Jané, M. Coma, J. Pons Prats, J. Bergadà

Rev. int. métodos numér. cálc. diseño ing. (2020). Vol. 36, (1), 4

Abstract
The paper focuses on the shape optimization, based on the resultant aerodynamic forces, of a simplified X-43 aircraft. The equations of oblique shock waves and Prandtl-Meyer expansion waves, along with the improvement of the aircraft geometry using a genetic algorithm optimisation, will allow to shape and optimize the external dimensions of the bi-dimensional simplified aircraft design. The main purpose of the optimisation is the reduction of the drag force while maintaining a sufficient lift to hold the weight of the aircraft. The optimization is undertaken at four different altitudes, obtaining for each altitude the most favourable aircraft shape to maximize the aircraft efficiency. The study can be extended to various possible aircraft weight configurations.
Abstract
The paper focuses on the shape optimization, based on the resultant aerodynamic forces, of a simplified X-43 aircraft. The equations of oblique shock waves and Prandtl-Meyer [...]
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Fuel cells state of the art
A. Jarauta, J. Pons Prats

(2009). Research Report, Nº PI340
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A semi-analytical model for droplet dynamics on the GDL surface of a PEFC electrode
A. Jarauta, M. Secanell, J. Pons Prats, P. Ryzhakov, S. Idelsohn, E. Oñate

Int. J. Hydrogen Energy (2015). Vol. 40 (15), pp. 5375-5383 (Preprint)

Abstract
Water management is one of the key factors in Proton Exchange Fuel Cell (PEFC) performance. The water produced within the fuel cell is evacuated through the gas channels, but at high current densities water can block the channel, thus limiting the current density generated in the fuel cell. A semi-analytical model of a water droplet emerging from a gas diffusion layer pore in a PEFC channel is developed. The transient model contains a detailed adhesion and drag force estimation model. Results show that the predicted values for both drag and surface tension force are higher than the results found in literature. The results for the detachment force are consistent with the experimental data available. Higher air velocity values lead to more deformation of the droplet and oscillation with lower frequency but higher amplitude. Similar effects have been identified when the liquid mass flow is increased, leading to faster detachment of the droplet.
Abstract
Water management is one of the key factors in Proton Exchange Fuel Cell (PEFC) performance. The water produced within the fuel cell is evacuated through the gas channels, [...]
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Contribution to the Definition of Non Deterministic Robust Optimization in Aeronautics Accounting with Variable Uncertainties
J. Pons Prats, G. Bugeda, F. Zarate

Personal Repository of Francisco Zarate (2011). 7

Abstract
Shape optimization is a largely studied problem in aeronautics. It can be applied to many disciplines in this field, namely efficiency improvement of engine blades, noise reduction of engine nozzles, or reduction of the fuel consumption of aircraft. Optimization for general purposes is also of increasing interest in many other fields. Traditionally, optimization procedures were based on deterministic methodologies as in Hamalainen et al (2000), where the optimum working point was fixed. However, not considering what happens in the vicinity of the defined working conditions can produce problems like loose of efficiency and performance. That is, in many cases, if the real working point differs from the original, even a little distance, efficiency is reduced considerably as pointed out in Huyse and Lewis (2001) Non deterministic methodologies have been applied to many fields (Papadrakakis, Lagaros and Tsompanakis, 1998; Plevris, Lagaros and Papadrakakis, 2005). One of the most extended nondeterministic methodologies is the stochastic analysis. The time consuming calculations required on Computational Fluid Dynamics (CFD) has prevented an extensive application of the stochastic analysis to shape optimization. Stochastic analysis was firstly developed in structural mechanics, several years ago. Uncertainty quantification and variability studies can help to deal with intrinsic errors of the processes or methods. The result to consider for design optimization is no longer a point, but a range of values that defines the area where, in average, optimal output values are obtained. The optimal value could be worse than other optima, but considering its vicinity, it is clearly the most robust regarding input variability. Uncertainty quantification is a topic of increasing interest from the last few years. It provides several techniques to evaluate uncertainty input parameters and their effects on the outcomes. This research presents a methodology to integrate evolutionary algorithms and stochastic analysis, in order to deal with uncertainty and to obtain robust solutions.
Abstract
Shape optimization is a largely studied problem in aeronautics. It can be applied to many disciplines in this field, namely efficiency improvement of engine blades, noise [...]
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Articles (Documents not available in Scipedia)

Numerical Study of Roughness and Contact Angle Effects on Water Transport in a Gas Channel
A Jarauta, T Chan, AZ Weber, P Ryzhakov, J Pons-Prats, M Secanell

Meeting Abstracts, 1644-1644, 2017
Analysis of uncertainty and variability in finite element computational models for biomedical engineering: characterization and propagation
N Mangado, G Piella, J Noailly, J Pons-Prats, MÁG Ballester

Frontiers in Bioengineering and Biotechnology 4, 2016
Ram-Air Parachute Simulation with Panel Methods and Staggered Coupling
E Ortega, R Flores, J Pons-Prats

Journal of Aircraft, 2016
On the application of the PFEM to droplet dynamics modeling in fuel cells
PB Ryzhakov, A Jarauta, M Secanell, J Pons-Prats

Computational Particle Mechanics, 1-11, 2016
Numerical study of droplet dynamics in a polymer electrolyte fuel cell gas channel using an embedded Eulerian-Lagrangian approach
A Jarauta, P Ryzhakov, M Secanell, PR Waghmare, J Pons-Prats

Journal of Power Sources 323, 201-212, 2016
Turbulent separated shear flow control by surface plasma actuator: experimental optimization by genetic algorithm approach
N Benard, J Pons-Prats, J Periaux, G Bugeda, P Braud, JP Bonnet, ...

Experiments in fluids 57 (2), 22, 2016
EU-China research cooperation in aeronautics technologies: GRAIN 2
G Bugeda Castelltort, Y Deng, JF Periaux, J Pons Prats

Aerodays2015, 1-19, 2015
Multi-Input Genetic Algorithm for Experimental Optimization of the Reattachment Downstream of a Backward-Facing-Step with Surface Plasma Actuator
N Benard, J Pons-Prat, J Periaux, G Bugeda, JP Bonnet, E Moreau

46th AIAA Plasmadynamics and Lasers Conference, 2957, 2015
Multilevel Monte-Carlo methods applied to the stochastic analysis of aerodynamic problems
G Bugeda Castelltort, J Pons Prats

CMN 2015 Congreso de Métodos Numéridos en Ingeniería, 1-18, 2015
A semi-analytical model for droplet dynamics on the GDL surface of a PEFC electrode
A Jarauta, M Secanell, J Pons-Prats, P Ryzhakov, SR Idelsohn, E Onate

international journal of hydrogen energy 40 (15), 5375-5383, 2015
Multi-objective design optimisation of a 3D-rail stamping process using a robust multi-objective optimisation platform (RMOP)
DS Lee, HG Espinoza Román, ÓA Fruitós Bickham, J Pons Prats

Computational Plasticity XII. Fundamentals and Applications, 1-12, 2013
Robust Design Optimization applied to aeronautics combining stochastic calculus with evolutionary algoritms
J Pons-Prats, G Bugeda, F Zarate, E Onate

REVISTA INTERNACIONAL DE METODOS NUMERICOS PARA CALCULO Y DISENO EN ..., 2012
Optimización robusta en aplicaciones aeronáuticas con la combinación de cálculo estocástico y algoritmos evolutivos
J Pons-Prats, G Bugeda, F Zárate, E Oñate

Revista Internacional de Métodos Numéricos para Cálculo y Diseño en ..., 2012
Stochastic and Robust design procedures applied to the optimization with uncertainties
J Pons Prats, G Bugeda Castelltort, JF Zárate Araiza, ...

EUROGEN 2011. Evolutionary methods for design, optimization and control ..., 2011
Robust design optimization in aeronautics using stochastic analysis and evolutionary algorithms
J Pons-Prats, G Bugeda, F Zárate, E Oñate

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of ..., 2011
Double Shock Control Bump design optimization using hybridised evolutionary algorithms
DS Lee, J Periaux, J Pons-Prats, G Bugeda, E Oñate

Evolutionary Computation (CEC), 2010 IEEE Congress on, 1-8, 2010
Robust Shape Optimization in Aeronautics using stochastic analysis and evolutionary algorithms
J Pons-Prats, G Bugeda, E Oñate

WCCM/APCOM, 2010
Robust shape optimization in aeronautics
J Pons-Prats, G Bugeda Castelltort, E Oñate Ibáñez de Navarra, F Zárate, ...

Eighth World Congress on Structural and Multidisciplinary Optimization, 1-16, 2009
Non-deterministic shape optimization in aeronautics
J Pons-Prats, E Oñate, F Zárate, G Bugeda, J Hurtado

12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 5827, 2008

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Documents published in Scipedia

Articles (Documents not available in Scipedia)

Numerical Study of Roughness and Contact Angle Effects on Water Transport in a Gas Channel

Analysis of uncertainty and variability in finite element computational models for biomedical engineering: characterization and propagation

Ram-Air Parachute Simulation with Panel Methods and Staggered Coupling

On the application of the PFEM to droplet dynamics modeling in fuel cells

Numerical study of droplet dynamics in a polymer electrolyte fuel cell gas channel using an embedded Eulerian-Lagrangian approach

Turbulent separated shear flow control by surface plasma actuator: experimental optimization by genetic algorithm approach

EU-China research cooperation in aeronautics technologies: GRAIN 2

Multi-Input Genetic Algorithm for Experimental Optimization of the Reattachment Downstream of a Backward-Facing-Step with Surface Plasma Actuator

Multilevel Monte-Carlo methods applied to the stochastic analysis of aerodynamic problems

A semi-analytical model for droplet dynamics on the GDL surface of a PEFC electrode

Multi-objective design optimisation of a 3D-rail stamping process using a robust multi-objective optimisation platform (RMOP)

Robust Design Optimization applied to aeronautics combining stochastic calculus with evolutionary algoritms

Optimización robusta en aplicaciones aeronáuticas con la combinación de cálculo estocástico y algoritmos evolutivos

Stochastic and Robust design procedures applied to the optimization with uncertainties

Robust design optimization in aeronautics using stochastic analysis and evolutionary algorithms

Double Shock Control Bump design optimization using hybridised evolutionary algorithms

Robust Shape Optimization in Aeronautics using stochastic analysis and evolutionary algorithms

Robust shape optimization in aeronautics

Non-deterministic shape optimization in aeronautics

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Quezon, Emer T. 12372

González, Michael Alvarez 343

ARAUJO, LEILSON 768

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