Jouke Hijlkema - Academia.edu (original) (raw)

Papers by Jouke Hijlkema

Research paper thumbnail of Progress in Solving Coupled Aerothermodynamics Issues Faced by Space Vehicles

/RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far fr... more /RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far from being fully understood. Among them, a number is concerned with other physical phenomena than pure ATD. This lecture is intended to present an updated view of the current knowledge about clearly identified ATD issues, with a special focus on these issues where ATD is coupled with other physical phenomena or scientific fields. Here, the phenomena of interest consist in aerothermo-chemistry, ATD modelling validation, numerical issues such as carbuncle or simultaneous computation of high-speed and very low speed flows such as in wakes and gaps, material behaviour involved in Thermal Protection System design, and high-temperature gas radiation appearing in high-speed flows. In each case, achievements and remaining questions are presented based on recent National and European projects.

Research paper thumbnail of Radiation heat transfer simulation platform PHARAON, description and first application to Mars aerocapture mission

Dans la perspective de futures missions d'exploration planétaire, l'échauffement radiatif des véh... more Dans la perspective de futures missions d'exploration planétaire, l'échauffement radiatif des véhicules spatiaux pendant l'entrée dans l'atmosphère doit être évaluée. C'était le cas en particulier pour la mission de retour d'échantillons martiens (MSR) envisagée par la NASA et le CNES. Au cours de cette étude, il a été mis en évidence que l'évaluation du flux radiatif sur l'arrière-corps de l'orbiteur MSR pendant la phase d'aérocapture constituait un problème critique vis-à-vis de la faisabilité du concept de véhicule sélectionné. C'est pourquoi le CNES décida de lancer une activité sur la simulation numérique du rayonnement conduisant notamment au développement de la plate-forme logicielle appelée PHARAON et présentée dans cette communication. Cette plate-forme permet d'estimer les flux de chaleur radiatif et convectif à la paroi d'un véhicule au cours d'une entrée dans l'atmosphère sur la base d'une approche découplée. Sa conception est générale et devrait permettre d'associer différents codes de mécanique des fluides numérique, différentes données spectrales et différents codes de transfert radiatif, pour peu que le format d'échange de données soit connu. La validation de la plate-forme est illustrée sur une configuration simplifiée de l'orbiteur MSR pour un point de trajectoire représentatif d'une aérocapture martienne. Les résultats montrent l'importance du flux radiatif par rapport au flux convectif, ainsi qu'une comparaison des résultats avec d'autres codes.

Research paper thumbnail of Development of the PHARAON platform and ONERA numerical solvers for gas radiation

The paper presents the PHARAON platform and the ONERA solvers developed to study gas radiation of... more The paper presents the PHARAON platform and the ONERA solvers developed to study gas radiation of high temperature gases during atmospheric re-entries. The platform aims at facilitating dataset interchange between the different solvers involved in a radiation calculation, using a clearly defined data structure and a general interpolation tool. The corresponding solvers are, at the present time, Navier-Stokes solvers and a radiative heat transfer solver using a Statistical Narrow-Band model for the CO and CO2 molecules. Aerothermodynamic computations on the testcase TC3-1 are presented as well as a first application of the interpolation tool.

Research paper thumbnail of A random particle method to simulate coalescence phenomena in dense liquid sprays

Lecture Notes in Physics, 1998

Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un sp... more Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un spray dense de gouttelettes liquides transportees par un Ccoulement gazeux. Notre modele repose sur l'hypothbse que toute collision donne lieu soit 9 un rebond tlastique soit Ft une coalescence. Nous montrons que l'operateur de collision obtenu possede des proprietes analogues B celui de Boltzmann et nous exploitons cette analogie pour construire, en suivant les idees de Babovski (v&r [l]), une m&ode particulaire aleatoire permettant de le discretiser.

Research paper thumbnail of Effects of Cavity on Thrust Oscillations in Subscale Solid Rocket Motors

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009

ABSTRACT

Research paper thumbnail of Numerically–Assisted Particle Size Distribution Measurements in Reduce-Scale Solid Rocked Motors

Journal of Propulsion and Power, 2015

Research paper thumbnail of DLR-ONERA accurate CFD support for the Pre-X project

During the development of Pre-X demonstrator supported by CNES , industrials are in charge of aer... more During the development of Pre-X demonstrator supported by CNES , industrials are in charge of aerodynamic and aerothermodynamic defintion and characterisation of the vehicle. For this preliminary phase of the project, most of the time industrials only used Euler computations associated to boundary layer, so that a lot of parametric analysis can be carried out and the feasibility of the project was globally checked. It is clear that deeper analyses for some critical trajectory points are required to overcome potential infeasibilities. The main objective of the accurate CFD support, provided by DLR and ONERA consists in assessing these high level objectives. Two critical issues are investigated. The heat fluxes level on the windward side of the body, the deflected flap in the hypersonic regime and the aerodynamic static margin at the end of the trajectory in the supersonic regime. Two relevant codes where used: the TAU code from DLR and CELHYO3D from ONERA. * The unstructured TAU code...

Research paper thumbnail of Progress in Solving Coupled Aerothermodynamics Issues Faced by Space Vehicles

/RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far fr... more /RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far from being fully understood. Among them, a number is concerned with other physical phenomena than pure ATD. This lecture is intended to present an updated view of the current knowledge about clearly identified ATD issues, with a special focus on these issues where ATD is coupled with other physical phenomena or scientific fields. Here, the phenomena of interest consist in aerothermo-chemistry, ATD modelling validation, numerical issues such as carbuncle or simultaneous computation of high-speed and very low speed flows such as in wakes and gaps, material behaviour involved in Thermal Protection System design, and high-temperature gas radiation appearing in high-speed flows. In each case, achievements and remaining questions are presented based on recent National and European projects.

Research paper thumbnail of Particle size distribution measurements in the Keldysh Research Centre experimental setup at ONERA

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011

Research paper thumbnail of Computation of Weakly Ionized Atmospheric Entry Flows Using an Extended Roe Scheme

Computational Fluid Dynamics 2004, 2006

... Entry Flows Using an Extended Roe Scheme Tristan Soubrié, Olivier Rouzaud, and Jouke Hylkema ... more ... Entry Flows Using an Extended Roe Scheme Tristan Soubrié, Olivier Rouzaud, and Jouke Hylkema ONERA,DMAE, BP 4025, 31055 Toulouse, France, rouzaud@onecert.fr 1 Introduction ... s=ion ρs Ms (6) Page 2. 806 Tristan Soubrié, Olivier Rouzaud, and Jouke Hylkema ...

Research paper thumbnail of Numerical Simulation of Radiative Heating for Atmospheric Reentry in Martian Atmosphere

Computational Fluid Dynamics 2004, 2006

Research paper thumbnail of Une méthode particulaire aléatoire reposant sur une équation cinétique pour la simulation numérique des sprays denses de gouttelettes liquides

Comptes Rendus de l'Académie des Sciences - Series I - Mathematics, 1997

ABSTRACT

Research paper thumbnail of A random particle method based on a kinetic equation for the numerical simulation of dense sprays of liquid droplets

Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un sp... more Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un spray dense de gouttelettes liquides transportees par un Ccoulement gazeux. Notre modele repose sur l'hypothbse que toute collision donne lieu soit 9 un rebond tlastique soit Ft une coalescence. Nous montrons que l'operateur de collision obtenu possede des proprietes analogues B celui de Boltzmann et nous exploitons cette analogie pour construire, en suivant les idees de Babovski (v&r [l]), une m&ode particulaire aleatoire permettant de le discretiser.

Research paper thumbnail of Progress in Solving Coupled Aerothermodynamics Issues Faced by Space Vehicles

/RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far fr... more /RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far from being fully understood. Among them, a number is concerned with other physical phenomena than pure ATD. This lecture is intended to present an updated view of the current knowledge about clearly identified ATD issues, with a special focus on these issues where ATD is coupled with other physical phenomena or scientific fields. Here, the phenomena of interest consist in aerothermo-chemistry, ATD modelling validation, numerical issues such as carbuncle or simultaneous computation of high-speed and very low speed flows such as in wakes and gaps, material behaviour involved in Thermal Protection System design, and high-temperature gas radiation appearing in high-speed flows. In each case, achievements and remaining questions are presented based on recent National and European projects.

Research paper thumbnail of Radiation heat transfer simulation platform PHARAON, description and first application to Mars aerocapture mission

Dans la perspective de futures missions d'exploration planétaire, l'échauffement radiatif des véh... more Dans la perspective de futures missions d'exploration planétaire, l'échauffement radiatif des véhicules spatiaux pendant l'entrée dans l'atmosphère doit être évaluée. C'était le cas en particulier pour la mission de retour d'échantillons martiens (MSR) envisagée par la NASA et le CNES. Au cours de cette étude, il a été mis en évidence que l'évaluation du flux radiatif sur l'arrière-corps de l'orbiteur MSR pendant la phase d'aérocapture constituait un problème critique vis-à-vis de la faisabilité du concept de véhicule sélectionné. C'est pourquoi le CNES décida de lancer une activité sur la simulation numérique du rayonnement conduisant notamment au développement de la plate-forme logicielle appelée PHARAON et présentée dans cette communication. Cette plate-forme permet d'estimer les flux de chaleur radiatif et convectif à la paroi d'un véhicule au cours d'une entrée dans l'atmosphère sur la base d'une approche découplée. Sa conception est générale et devrait permettre d'associer différents codes de mécanique des fluides numérique, différentes données spectrales et différents codes de transfert radiatif, pour peu que le format d'échange de données soit connu. La validation de la plate-forme est illustrée sur une configuration simplifiée de l'orbiteur MSR pour un point de trajectoire représentatif d'une aérocapture martienne. Les résultats montrent l'importance du flux radiatif par rapport au flux convectif, ainsi qu'une comparaison des résultats avec d'autres codes.

Research paper thumbnail of Development of the PHARAON platform and ONERA numerical solvers for gas radiation

The paper presents the PHARAON platform and the ONERA solvers developed to study gas radiation of... more The paper presents the PHARAON platform and the ONERA solvers developed to study gas radiation of high temperature gases during atmospheric re-entries. The platform aims at facilitating dataset interchange between the different solvers involved in a radiation calculation, using a clearly defined data structure and a general interpolation tool. The corresponding solvers are, at the present time, Navier-Stokes solvers and a radiative heat transfer solver using a Statistical Narrow-Band model for the CO and CO2 molecules. Aerothermodynamic computations on the testcase TC3-1 are presented as well as a first application of the interpolation tool.

Research paper thumbnail of A random particle method to simulate coalescence phenomena in dense liquid sprays

Lecture Notes in Physics, 1998

Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un sp... more Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un spray dense de gouttelettes liquides transportees par un Ccoulement gazeux. Notre modele repose sur l'hypothbse que toute collision donne lieu soit 9 un rebond tlastique soit Ft une coalescence. Nous montrons que l'operateur de collision obtenu possede des proprietes analogues B celui de Boltzmann et nous exploitons cette analogie pour construire, en suivant les idees de Babovski (v&r [l]), une m&ode particulaire aleatoire permettant de le discretiser.

Research paper thumbnail of Effects of Cavity on Thrust Oscillations in Subscale Solid Rocket Motors

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009

ABSTRACT

Research paper thumbnail of Numerically–Assisted Particle Size Distribution Measurements in Reduce-Scale Solid Rocked Motors

Journal of Propulsion and Power, 2015

Research paper thumbnail of DLR-ONERA accurate CFD support for the Pre-X project

During the development of Pre-X demonstrator supported by CNES , industrials are in charge of aer... more During the development of Pre-X demonstrator supported by CNES , industrials are in charge of aerodynamic and aerothermodynamic defintion and characterisation of the vehicle. For this preliminary phase of the project, most of the time industrials only used Euler computations associated to boundary layer, so that a lot of parametric analysis can be carried out and the feasibility of the project was globally checked. It is clear that deeper analyses for some critical trajectory points are required to overcome potential infeasibilities. The main objective of the accurate CFD support, provided by DLR and ONERA consists in assessing these high level objectives. Two critical issues are investigated. The heat fluxes level on the windward side of the body, the deflected flap in the hypersonic regime and the aerodynamic static margin at the end of the trajectory in the supersonic regime. Two relevant codes where used: the TAU code from DLR and CELHYO3D from ONERA. * The unstructured TAU code...

Research paper thumbnail of Progress in Solving Coupled Aerothermodynamics Issues Faced by Space Vehicles

/RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far fr... more /RESUME Aerothermodynamics (ATD) for Space Vehicles is raising a number of issues that are far from being fully understood. Among them, a number is concerned with other physical phenomena than pure ATD. This lecture is intended to present an updated view of the current knowledge about clearly identified ATD issues, with a special focus on these issues where ATD is coupled with other physical phenomena or scientific fields. Here, the phenomena of interest consist in aerothermo-chemistry, ATD modelling validation, numerical issues such as carbuncle or simultaneous computation of high-speed and very low speed flows such as in wakes and gaps, material behaviour involved in Thermal Protection System design, and high-temperature gas radiation appearing in high-speed flows. In each case, achievements and remaining questions are presented based on recent National and European projects.

Research paper thumbnail of Particle size distribution measurements in the Keldysh Research Centre experimental setup at ONERA

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011

Research paper thumbnail of Computation of Weakly Ionized Atmospheric Entry Flows Using an Extended Roe Scheme

Computational Fluid Dynamics 2004, 2006

... Entry Flows Using an Extended Roe Scheme Tristan Soubrié, Olivier Rouzaud, and Jouke Hylkema ... more ... Entry Flows Using an Extended Roe Scheme Tristan Soubrié, Olivier Rouzaud, and Jouke Hylkema ONERA,DMAE, BP 4025, 31055 Toulouse, France, rouzaud@onecert.fr 1 Introduction ... s=ion ρs Ms (6) Page 2. 806 Tristan Soubrié, Olivier Rouzaud, and Jouke Hylkema ...

Research paper thumbnail of Numerical Simulation of Radiative Heating for Atmospheric Reentry in Martian Atmosphere

Computational Fluid Dynamics 2004, 2006

Research paper thumbnail of Une méthode particulaire aléatoire reposant sur une équation cinétique pour la simulation numérique des sprays denses de gouttelettes liquides

Comptes Rendus de l'Académie des Sciences - Series I - Mathematics, 1997

ABSTRACT

Research paper thumbnail of A random particle method based on a kinetic equation for the numerical simulation of dense sprays of liquid droplets

Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un sp... more Nous presentons dans cette Note une equation cinetique prenant en compte les collisions dam un spray dense de gouttelettes liquides transportees par un Ccoulement gazeux. Notre modele repose sur l'hypothbse que toute collision donne lieu soit 9 un rebond tlastique soit Ft une coalescence. Nous montrons que l'operateur de collision obtenu possede des proprietes analogues B celui de Boltzmann et nous exploitons cette analogie pour construire, en suivant les idees de Babovski (v&r [l]), une m&ode particulaire aleatoire permettant de le discretiser.