Reynald Bur

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• PhD Hab.
• Research Director at Office National d'Études et de Recherches Aérospatiales

Transition measurements have been obtained through two experimental campaigns conducted independently by the German Aerospace Center and the French Aerospace Lab with the French Alternative Energies and Atomic Energy Commission on subscale models of the BOLT-1 flight experiment geometry. This paper details a cross-facility comparison of measurement...

A novel bleed model derived from a comprehensive dataset generated by a numerical parametric study is introduced. This model discretely represents the hole contour on a porous patch, allowing the mesh to incorporate the hole pattern. This approach enables the extraction of the tangential Mach number at the outflow boundary condition within the RANS...

A comprehensive investigation into the flow over a hollow-cylinder and [Formula: see text] flare has been conducted at Mach 5 with transitional Reynolds numbers. Experiments of two similar models have been conducted in LT5 at the University of Arizona and R2Ch at ONERA. Considerable differences in reattachment behavior were observed from infrared t...

The static and dynamic interaction of a normal shock wave (upstream Mach number 1.35) with a compliant wall is characterized experimentally by schlieren visualizations and an optical displacement sensor. Depending on the location of the shock wave along the compliant wall, three different regimes of interaction are found: large-amplitude synchroniz...

This paper presents a comprehensive experimental and numerical investigation into the control of boundary layers using porous bleed systems. The study focuses on both supersonic and subsonic flow regimes, as well as on the control of shock-wave/boundary-layer interactions. By simplifying this complex problem into two separate scenarios, the researc...

A comprehensive investigation into the flow over a Hollow-Cylinder/Flare has been conducted at Mach 5 with Re ≈ 11 × 10 5 and a flare deflection = 15 •. Experiments of two similar models have been conducted in LT5 at the University of Arizona (Tucson, USA) and R2Ch at ONERA (Meudon, France). Despite similar non-dimensional scaling of the models, a...

Transition measurements have been obtained through two experimental campaigns conducted independently by the German Aerospace Center and the French Aerospace Lab with the French Alternative Energies and Atomic Energy Commission on subscale models of the BOLT-1 flight experiment geometry. This paper details a cross-facility comparison of measurement...

This paper presents a comprehensive experimental and numerical investigation into the control of boundary layers using porous bleed systems. The study focuses on both supersonic and subsonic flow regimes, as well as on the control of shock-wave/boundary-layer interactions. By simplifying this complex problem into two separate scenarios, the researc...

Porous bleed systems are a common technique to control shock-/boundary-layer interactions and/or supersonic boundary layers. However, the influence of various design parameters is still unknown. Even though porous bleed models are required to minimize the costs of the design process, they often do not include parameter effects. In the present study...

Porous bleed systems are widely used to mitigate the shock-induced boundary layer separation, e.g., in supersonic air intakes. However, the complex geometry makes simulations expensive and motivates the application of suitable models. Existing models are based on applying a continuous blowing/suction boundary condition (continuous porosity) along t...

This paper aims to evaluate the prediction accuracy of various porous bleed models on two flow cases of particular interest for supersonic applications: turbulent boundary layer bleeding and control of shock-boundary layer interactions. A thorough literature review was conducted to select the most relevant models. The models were then implemented a...

The interaction of a normal shock-wave (upstream Mach number 1.35) with a compliant wall is characterized experimentally by schlieren visualizations and an optical displacement sensor. Depending on the location of the shock-wave along the compliant wall, three different regimes of interaction are found: large-amplitude synchronized regime, small-am...

Porous bleed systems are a common technique to control shock-boundary layer interactions and/or supersonic boundary layers. However, the influence of various design parameters is still unknown. Even though bleed models are required to minimize the costs of the design process, they often do not include parameter effects. In the present study, the ef...

This study presents simulations and experiments on the effect of porous bleed systems on a supersonic turbulent boundary layer at a Mach number of M=1.6. The results indicate a good fit between the RANS simulations and the experiments based on LDV, BOS, and pressure measurements. The numerical simulations well capture the overall flow topology. Bot...

The Shock/Boundary Layer Interaction (SBLI) over a rigid plate with an upstream 1.35 Mach number is characterized experimentally by unsteady pressure measurements and schlieren visualizations. Spectral Proper Orthogonal Decomposition (SPOD) is used on the schlieren videos to characterize the flow. The shock displacement spectrum is then used to cho...

In this paper, several existing porous bleed models are implemented intothe in-house RANS-solver elsA, and their performance are evaluated ontwo different flow cases. Reference simulations are performed to evalu-ate the accuracy of the applied bleed models and to show the lack ofmodeling different plate geometries. The models significantly differ i...

In this paper, several existing porous bleed models are implemented into the in-house RANS-solver elsA, and their performance are evaluated on two different flow cases. Reference simulations are performed to evaluate the accuracy of the applied bleed models and to show the lack of modeling different plate geometries. The models significantly differ...

Porous bleed systems are widely used to mitigate the shock-induced boundary layer separation, e.g., in supersonic air intakes. However , the complex geometry makes simulations expensive and motivates the application of suitable models. Existing models are based on applying a continuous blowing/suction boundary condition (continuous porosity) along...

Porous bleed systems are a common technique to control shock-boundary layer interactions and/or supersonic boundary layer. However, the influence of various design parameters is still unknown. Even though bleed models are required to minimize the costs of the design process, they often do not include parameter effects. In the present study, the eff...

Porous bleed systems are widely used to mitigate the shock-induced boundary layer separation, e.g., in supersonic air intakes. However, the complex geometry makes simulations expensive and motivates the application of suitable models. In this paper, seven porous bleed models are implemented as boundary conditions in the in-house compress-ible RANS...

Transitional shockwave/boundary layer interactions (SBLI) are studied experimentally. Experiments are conducted on a hollow-cylinder flare model in the R2Ch blowdown facility at a Mach number of 5 for three different Reynolds numbers in the transitional regime. Unsteady wall pressure measurements are conducted along with mean and unsteady heat flux...

A high-fidelity simulation of the massively separated shock/transitional boundary layer interaction caused by a 15-degrees axisymmetrical compression ramp is performed at a free stream Mach number of 6 and a transitional Reynolds number. The chosen configuration yields a strongly multiscale dynamics of the flow as the separated region oscillates at...

A high-fidelity simulation of the shock/transitional boundary layer interaction caused by a 15° axisymmetrical compression ramp is performed at a free stream Mach number of 5 and a transitional Reynolds number. The inlet of the computational domain is perturbed with a white noise in order to excite convective instabilities. Coherent structures are...

In order to be able to judge the effectiveness of transition induction in WP-2, reference flow cases were planned in WP-1. There are two obvious reference cases—a fully laminar interaction and a fully turbulent interaction. Here it should be explained that the terms “laminar” and “turbulent” interaction refer to the boundary layer state at the begi...

An important goal of the TFAST project was to study the effect of the location of transition in relation to the shock wave on the separation size, shock structure and unsteadiness of the interaction area. Boundary layer tripping (by wire or roughness) and flow control devices (Vortex Generators and cold plasma) were used for boundary layer transiti...

Flow control of separation caused by transonic shock-wave/boundary-layer interaction (SWBLI) is investigated. The control of the unsteadiness associated with SWBLI is not an objective of this paper. A SWBLI in a transonic channel is considered, and Reynolds-averaged Navier–Stokes simulations are carried out to compute the flow in the test section....

A high-fidelity simulation of the shock/transitional boundary layer interaction caused by a 15° axisymmetrical compression ramp is performed at a free stream Mach number of 5 and a transitional Reynolds number. The inlet of the computational domain is perturbed with a white noise in order to excite convective instabilities. Coherent structures are...

Flow control of separation caused by transonic shock-wave/boundary-layer interaction (SWBLI) is investigated. The control of the unsteadiness associated with SWBLI is not an objective of this paper. A SWBLI in a transonic channel is considered, and Reynolds-averaged Navier–Stokes simulations are carried out to compute the flow in the test section....

A high-fidelity simulation of the shock/transitional boundary layer interaction caused by a 15-degrees axisymmetrical compression ramp is performed at a freestream Mach number of 5 and a transitional Reynolds number. The inlet of the computational domain is perturbed with a white noise in order to excite convective instabilities. Coherent structure...

Flow control of separation caused by transonic shock-wave / boundary-layer interaction (SWBLI) is investigated. The control of the unsteadiness associated with SWBLI is not an objective of this paper. A SWBLI in a transonic channel is considered and RANS simulations are carried out to compute the flow in the test section. The massive separation due...

Femtosecond lasers can form long plasma filaments over distances ranging from several centimetres to several meters which can be used advantageously for high speed flow control, in particular for drag reduction. Recently the first experimental demonstration of femtosecond energy deposition in a wind tunnel has been reported. This paper completes th...

In this work, flow control of transonic shock wave boundary layer interactions is investigated. A wind-tunnel experiment featuring the Délery bump is considered and RANS simulations are carried out to compute the flow inside the test section. The massive separation due to shock wave / boundary layer interaction is controlled by fluidic Vortex Gener...

A two-dimensional analysis of the resolvent spectrum of a Mach 1.6 transitional boundary layer impacted by an oblique shock wave is carried out. The investigation is based on a two-dimensional mean flow obtained by a RANS model that includes a transition criterion. The goal is to evaluate whether such a low cost RANS based resolvent approach is cap...

When a flying object becomes supersonic, a concomitant increase in drag leads to a considerable rise in fuel consumption. We show experimentally that an embarked terawatt femtosecond laser can significantly decrease this drag. We measured a 50% transient reduction of drag on a test model placed in a supersonic wind tunnel at Mach 3. This effect was...

The goal of this study is to demonstrate experimentally the “Laser Spike” concept in a supersonic flow. The “Laser Spike” uses a thin filament of plasma created by a femtosecond laser. This plasma filament formed by the TeraWatt laser pulse acts as a linear energy deposition upstream of the shock wave created by a blunt body. It has been found that...

In this paper the RINGO (“Research Infrastructures - Needs, Gaps and Overlaps”) project and its methodology as well as initial findings will be presented. RINGO is a Coordination and Support Action funded by the European Commission under H2020 aimed at delivering a cohesive and coordinated approach for the identification and assessment of the needs...

The Flightpath 2050 (FP2050) strategy document has provided Europe with a vision for aviation and air transportation, identifying goals for the research community and policy makers alike. In order to achieve these challenging long-term goals, it is imperative to ensure that the required infrastructure for research activities addressing these challe...

Shock-wave/boundary layer interaction plays a major role in any circumstances where the flow becomes supersonic, either locally or in totality. This phenomenon is not clearly understood when the transitional regime (from laminar to turbulent) of the boundary layer appears during the interaction process, which is the case for compressor or turbine c...

This paper presents an application of the pressure-sensitive paint technique to investigate two-dimensional unsteady flow in a transonic channel. This work is a contribution to the study of the transonic interaction between an oscillating shock wave and a separated boundary layer in a channel flow. The shock-wave oscillation is forced by the period...

A transonic interaction between a shock wave and a turbulent boundary layer is experimentally and theoretically investigated. The configuration is a transonic channel flow over a bump, where a shock wave causes the separation of the boundary layer in the form of a recirculating bubble downstream of the shock foot. Different experimental techniques...

A transitional shock wave / boundary layer interaction at M=1.6 is investigated using experimental and numerical approaches. A flat plate apparatus installed in a supersonic wind tunnel serves as the basis of the study. Schlieren visualizations and measurements of the heat transfers at the surface of the flat plate provide a characterization of the...

This paper presents the results of a coupled experimental and numerical study aimed at evaluating the influence of typical aircraft surface imperfections on the flat-plate drag production in fully turbulent conditions. A test campaign involving high-level measurement techniques, such as microdrag evaluation, near-wall laser Doppler velocimetry, and...

This paper has the objective to present an overview of recent experimental studies conducted in the S3Ch transonic wind tunnel of the ONERA Meudon centre. Experimental investigations have been carried out on a civil transport aircraft power plant configuration to point out the complex wing / pylon / nacelle interference. Control of turbulent buffet...

The present study is aimed to analyse the effect of passive vortex generators in a transonic interaction between a shock-wave and a turbulent boundary layer in a channel flow at Mach number M = 1.45. Control of the boundary layer detachment downstream of the shock is obtained thanks to momentum transfer given by passive control devices, mechanical...

A transonic interaction between a shock wave and a turbulent boundary layer in a Mach 1.4 channel flow is experimentally and theoretically investigated. The configuration is a well documented transonic flow over a bump, where a strong shock wave causes the separation of the boundary layer and a recirculating bubble is observed downstream of the sho...

This paper presents the results of a coupled experimental and numerical study aimed at evaluating the influence of usual surface imperfections on the flat plate drag production. A test campaign involving high level measurement techniques such as micro drag evaluation, near wall laser Doppler velocimetry and oil film interferometry has been carried...

The control of the transonic buffet phenomenon over a half-model with a swept wing has been investigated in the S3Ch wind tunnel of the ONERA Meudon center in the framework of ONERA’s joint research project BUFET’N Co. A fine description of the buffet characteristics in the uncontrolled configuration is first given as a reference. Various steady an...

A transonic interaction between a steady shock wave and a turbulent boundary layer in a Mach 1.4 channel flow is experimentally investigated by means of particle image velocimetry (PIV). In the test section, the lower wall is equipped with a contour profile shaped as a bump allowing flow separation. The transonic interaction, characterized by the e...

Fluid mechanics and Aerodynamics exercises with corrections.

This paper presents an application of the Pressure Sensitive Paint (PSP) technique to investigate two-dimensional unsteady flow in a transonic channel. This work takes place in the study of the transonic interaction between an oscillating shock-wave and a separated boundary layer in a channel flow. Oscillation of the shock-wave is forced thanks to...

The purpose of the present experimental study is to test the effects of control devices – mechanical vortex generators (VGs) – both on a steady shock wave and on a forced shock oscillation configurations interacting with a separated boundary layer. Oscillation of the shock wave is forced thanks to a periodic variation of the downstream throat secti...

An experimental study was conducted in a transonic channel to control by mechanical vortex generator devices the strong interaction between a shock wave and a separated turbulent boundary layer. Control devices—co-rotating and counter-rotating vane-type vortex generators—were implemented upstream of the shock foot region and tested both on a steady...

This article is devoted to the experimental works carried out in the R2Ch blow-down wind tunnel in the framework of the atmospheric re-entry PRE-X demonstrator program and to the fundamental studies performed on a hollow cylinder-flare relative to crucial problem of the transitional shock-wave/boundary-layer interaction. Shock-wave/boundary-layer i...

For the last twenty to twenty-five years, a complete structured research programme has been defined at Onera for addressing 2D buffet control on a rigid airfoil. This research programme has comprised very detailed complementary experimental and numerical studies, aiming at achieving buffet control using either an open-type or a closed-type loop app...

The purpose of the present study is to investigate two-dimensional unsteady transonic flows in a channel with a sonic throat and a moderately strong normal shock downstream of the throat. The aim of the present work is to obtain a precise description of the unsteady flow in order to characterize the evolution of the boundary layer and the shock in...

The purpose of the present study is to analyze the unsteady aspects of the transonic interaction between an oscillating shock-wave and a separated boundary layer in a channel flow. Oscillation of the shock-wave is forced thanks to a periodic variation of the downstream throat section given by a rotating elliptical shaft located near this throat, in...

This paper gives an extensive presentation of the accessible experimental data bank of the ONERA Fundamental/Experimental Aerodynamics Department concerning high speed flows. Sophisticated non-intrusive measurements (3-component Laser Velocimetry, Particle Image Velocimetry, Coherent Anti-Stokes Raman Scattering, Pressure Sensitive Paint), flow vis...

At the beginning of 2000, ONERA launched an internal project (PRF: Projet de Recherche Fédérateur) aimed at investigating a few aerodynamic problems linked to the future supersonic aircraft. Five topics are studied: - Laminar-turbulent transition and laminar flow control, - Development of a “quiet” supersonic wind tunnel, - Turbulent flows at high...

An experimental and numerical study on the Mars Pathfinder aeroshell vehicle has been carried out in the framework of an agreement between ONERA and NASA. The experimental work was performed in the ONERA R5Ch hypersonic wind tunnel. Flowfield visualizations and heat-flux measurements along the model have been obtained. Numerical simulations have be...

The purpose of the present study is to investigate two-dimensional unsteady transonic flows in a channel with a sonic throat and a moderately strong normal shock downstream of the throat. The aim of the present work is to obtain a precise description of the unsteady flow in order to characterize the evolution of the boundary layer and the shock in...

The purpose of the present study is to investigate two-dimensional unsteady transonic flows in a channel with a sonic throat and a moderately strong normal shock downstream of the throat. The aim of the present work is to obtain a precise description of the unsteady flow in order to characterize the evolution of the boundary layer and the shock in...

The purpose of the present study is to investigate 2D unsteady transonic flows in a channel with a sonic throat and a moderately strong normal shock downstream of the throat. The aim of the present work is to obtain a precise description of the unsteady flow in order to characterize the evolution of the boundary layer and the shock in space and tim...

Experimental and numerical studies of the laminar shock-wave/boundary-layer interaction occurring past a hollow cylinder flare model in a Mach 10 air flow at zero incidence were conducted. Flowfield density measurements were performed by detecting x-ray emissions from the gas produced by electron-beam impact. A solution was found to make these meas...

The aim of this study was to investigate in detail the flow field resulting from transonic shock wave / boundary layer interactions under control conditions. Several control techniques have been investigated: 1) active control device, which consists in sucking a part of the boundary layer flow through a slot, 2) hybrid control device, which is a co...

The importance of systems aimed at controlling shock-wave/boundary-layer interactions appears for transport aircraft in the domain of transonic external flows and for supersonic air intakes in the domain of internal flows. The calibration of these systems requires powerful predictive calculation methods and therefore improvements in the modelling o...

Experimental investigations have been achieved in the ONERA research facilities of the Chalais-Meudon Center in order to validate design tools used for the definition of a scramjet for a hypersonic spacecraft. Aerodynamic interactions occurring on such a spacecraft have been thoroughly studied, notably 1) the shock/shock interactions ahead of the a...

In high speed flow, the existence of shock waves most often entails either drag increase or efficiency losses. A major cause of performance degradation is the interaction of the shock with a boundary layer. Then complex phenomena occur which contributes to increase friction losses, especially if the shock is strong enough to separate the boundary l...

This article deals with the research performed in the framework of the internal ONERA Hyperenthalpic Hypersonic Project. This project involved fifteen researchers specialised in different domains, which are the following: fundamental studies on shock-wave and shock/boundary layers interactions; study of the laminar/turbulent transition; real gas ef...

Control devices applied to a turbulent shock-wave / boundary-layer interaction have been investigated by considering a two-dimensional channel flow. The efficiency of active control devices, which consist in sucking a part of the boundary-layer through a slot, is compared respectively with those of a hybrid control device, which is a combination of...

Most internal flows develop a highly three-dimensional structure difficult to apprehend. In particular, the separation phenomenon in three-dimensional flow is far more difficult to grasp and to define than in two-dimensional situations. In fact, a clear physical understanding of this phenomenon must be based upon a rational analysis of the flow fie...

Control devices applied to a turbulent shock-wave / boundary-layer interaction have been investigated by considering a two-dimensional channel flow. The efficiency of active control devices, which consist in sucking a part of the boundary-layer through a slot, is compared with those of hybrid control devices, which are combinations of a passive con...

This article is devoted to an experimental and numerical study of shock wave/boundary layer interaction in hypersonic laminar flow (M = 10). The experiment was performed in the ONERA R5Ch wind tunnel on a hollow cylinder flare. The flow stream delivered by the R5Ch wind tunnel produces physical conditions which justify both the theoretical approach...

Passive control applied to a turbulent shock wave/boundary-layer interaction has been investigated by considering a two-dimensional channel flow. The field has been probed in great detail by using a two-component laser Doppler velocimetry system to execute mean velocity and turbulence measurements. Four different perforated plates have been conside...

Passive control applied to a turbulent shock wave/boundary layer interaction has been investigated by considering a two-dimensional channel flow. The field resulting from application of passive control has been probed in great detail by using a two-component laser Doppler velocimetry system to execute mean velocity and turbulence measurements. Four...

Passive control applied to a turbulent shock wave/boundary-layer interaction has been investigated by considering a two-dimensional channel flow. The field has been probed in great detail by using a two-component laser Doppler velocimetry system to execute mean velocity and turbulence measurements. Four different perforated plates have been conside...

Passive control applied to a turbulent shock wave/boundary layer interaction has been investigated by considering a two-dimensional channel flow. The field resulting from application of passive control has been probed in detail by using a two-component LDV system to execute mean velocity and turbulence measurements. Four different perforated plates...

The article deals with both experimental and numerical studies of the laminar shock wave/boundary layer interaction occuring past a hollow cylinder flare model without incidence in a Mach 10 flow. As far as the experimental study is concerned, the flow has been characterized by both field and wall visualizations. The repercussions at the wall of th...

The techniques for controlling shock wave/turbulent boundary layer interaction are reviewed. A passive control device makes it possible to improve the performance of airfoils at transonic velocities. An interaction subjected to passive control was performed in a transonic channel. The flow is described by means of Schlieren visualization, measureme...

A detailed analysis of an interaction subjected to passive control was performed in a transonic channel, with consideration of the following parameters: shock location with respect to the cavity, porosity and hole diameter of the perforated plate, cavity depth. The flow was qualified by schlieren visualizations, wall pressure measurements and 2D la...

Different techniques used to control the interaction between a shock wave and a turbulent boundary layer show that passive control tends to improve profile performance at transonic velocities. An analysis of an interaction subjected to passive control was performed in a transonic channel, taking into account the following parameters: shock location...