Fulvio Sartor

The French Aerospace Lab ONERA | ONERA · DAAP- ACI

This paper presents an investigation of the aerodynamic field and the acoustic signature of a mixed-stream coaxial jet, representative of a low-bypass ratio engine, installed on a T-tail configuration, typical of business jets. Numerical simulations and associated acoustic analysis have been performed by ONERA in the frame of the European collabora...

This article presents the numerical computations performed at ONERA for the Seventh AIAA Drag Prediction Workshop. By introducing Reynolds numbers up to 30 million closer to the flight conditions, greater lift levels beyond the design point, and time-accurate simulations, this new session has allowed the previous studies to be extended. The Common...

This paper presents scale resolving simulations for jet noise prediction of configurations of increasing complexity. In order to deal with geometrically complex configurations, the unstructured mesh approach is considered in this work, which is a departure from previous studies by the Authors. Therefore, the simulation methodology based on Zonal De...

This paper presents the aerodynamic performance study of an isolated ultra-high bypass ratio turbofan engine. The performance assessment methodology relies on an exergy balance, computed using the ONERA FFX software on the basis of RANS CFD solutions. The study first investigates aspects associated with the computational strategy used to simulate e...

This paper will present the main results of the aerodynamic design and analysis for flow control applied to trailing edge of wings and profiles. This work has been conducted in the framework of the European project AFLoNext aiming at developing technologies allowing for an improvement of the performance and loads situation in the operational domain...

This paper will present the main results of the aerodynamic design and analysis for flow control applied to trailing edge of wings and profiles. This work has been conducted in the framework of the European project AFLoNext aiming at developing technologies allowing for an improvement of the performance and loads situation in the operational domain...

The presentation Shows the result of a 4 year Research activity on trailing edge buffet control by fluidic Gurneys and micro-circulation-control in the scope of the European Project AFLoNext

This paper presents a numerical study of the transonic flow over a half wing–body configuration representative of a large civil aircraft. The Mach number is close to cruise conditions, whereas the high angle of attack causes strong separation on the suction side of the wing. Results indicate the presence of shock-wave oscillations inducing unsteady...

This paper will present the main results of the aerodynamic design and analysis for flow control applied to trailing edge of wings and profiles. This work has been conducted in the framework of the European Project AFLoNext aiming at developing technologies allowing for an improvement of the performance and loads situation in the operational domain...

Purpose The purpose of this paper is to discuss a numerical study of the flow over a wing representative of a large civil aircraft at cruise condition. For each Mach number considered, the numerical simulations indicate that critical angle of attack exists where the separated region increases in size and begins to oscillate. This phenomenon, known...

This paper presents a numerical study of a double-stream coaxial jet representative of a high-bypass ratio engine. The configuration is first investigated in clean conditions using a turbulence-resolving simulation, validated against experimental data from the CoJeN European collaborative project. Then, an active flow-control technique is proposed,...

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 transonic flow over the OAT15A supercritical profile is considered. The interaction between the shock wave and the turbulent boundary layer is investigated through numerical simulation and global stability analysis for a wide range of angles of attack. Numerical simulations are in good agreement with previous studies and manage to reproduce the h...

This paper presents a numerical study of the transonic flow over a half wing-body configuration representative of a large civil aircraft. Results indicate the presence of shock-wave oscillations that induce unsteady loads and can cause serious damage to the aircraft. The work focusses on the onset of the buffet unsteadiness and its control by means...

This paper presents a numerical study of the transonic flow over a half wing-body configuration representative of a large civil aircraft. The Mach number is close to cruise conditions, while the high angle of attack causes massive separation on the suction side of the wing. Results indicate the presence of shock-wave oscillations inducing unsteady...

A numerical study of the flow over a wing representative of a large civil aircraft at cruise condition is discussed. Reynolds-averaged Navier-Stokes simulations are conducted on a half wing-body configuration, at different Mach numbers and angles of attack. For small angles, the shock-induced separation is limited and the simulations converge towar...

This paper presents a numerical study of transonic flow over a wing representative of a large transport aircraft. Reynolds–averaged Navier–Stokes simulations are conducted on a half wing-body configuration, with a Mach number close to cruise conditions and different angles of attack. The flow physics are discussed with particular attention to the separ...

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 and a recirculating bubble is observed downstream of the shock foot. First, the mean flow is experimen...

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...

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...