François Lesage

ORCID: 0000-0003-0628-4078
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About
Contact & Profiles
Research Areas
  • Heat and Mass Transfer in Porous Media
  • Advanced Control Systems Optimization
  • Fluid Dynamics and Turbulent Flows
  • Process Optimization and Integration
  • Fluid Dynamics and Mixing
  • Computational Fluid Dynamics and Aerodynamics
  • Gas Dynamics and Kinetic Theory
  • Plasma and Flow Control in Aerodynamics
  • Fault Detection and Control Systems
  • Fuel Cells and Related Materials
  • Rocket and propulsion systems research
  • Iron and Steelmaking Processes
  • Wind and Air Flow Studies
  • Fluid Dynamics and Vibration Analysis
  • Catalysis and Hydrodesulfurization Studies
  • Electrical and Bioimpedance Tomography
  • Vibration and Dynamic Analysis
  • Topology Optimization in Engineering
  • Rheology and Fluid Dynamics Studies
  • Nanofluid Flow and Heat Transfer
  • Advanced Mathematical Modeling in Engineering
  • Guidance and Control Systems
  • Thermochemical Biomass Conversion Processes
  • Petroleum Processing and Analysis
  • Hydraulic Fracturing and Reservoir Analysis

Université de Lorraine
2012-2023

Centre National de la Recherche Scientifique
2008-2023

Laboratoire Réactions et Génie des Procédés
2013-2023

Defence Research and Development Canada
2005-2014

Laboratoire de Génie Chimique
1998-2010

Bombardier Recreational Products (Canada)
2000

University of British Columbia
1987

10.1016/0167-6105(87)90019-5 article EN Journal of Wind Engineering and Industrial Aerodynamics 1987-01-01

Recently, grid fins have been receiving increasing attention as a practical and efficient means of controlling missile trajectory. Preliminary studies at IAR demonstrated that modern CFD methods can be used for computing flows past complex fin type configurations, these bring improved predictions over the earlier vortex lattice and/or shock expansion methods. aerodynamic coefficients assembly, with without fairing ramp, would provide direct evaluating effect At this stage, investigations are...

10.2514/6.2000-987 article EN 38th Aerospace Sciences Meeting and Exhibit 2000-01-10

Two wire mesh tomography devices and a liquid collector were used to study the influence of gas flow rate on distribution when fluids top reactor is ensured by perforated plate. In opposition most studies realized other authors, conditions in which has negative impact evidenced. Indeed, obtained results show that depends quality initial distribution, as forces "respect" imposed at reactor. Finally, comparison between two measuring techniques shows limitations improper conclusions its use could lead.

10.1021/ie8001155 article EN Industrial & Engineering Chemistry Research 2008-06-25

Two research institutes TNO Defence, Security and Safety DRDC-Valcartier have worked together on the improvement of modeling simulation tools for functioning supersonic air intakes realistic ramjet engines tactical missiles. The emphasis laid complex rectangular intake designs making use an internal bleed system incorporating at off-design conditions (below above design Mach number angle-of-attack with respect to freestream velocity). In order generate performance data validated...

10.2514/6.2009-5076 article EN 2009-08-02

10.1016/j.cep.2004.08.009 article EN Chemical Engineering and Processing - Process Intensification 2004-12-15

Abstract During the Roman period, glass window panes could be made by two processes: they may cast, or blown cylinder‐blown method. The thermal history and fictive temperatures ( T f ) of both sides pane are different depending on process employed. wavenumber some Raman peaks depends temperature studied sample. Calibration curves drawn with annealed samples, which used to determine sides. This method is applied success archaeological obtain their and, this way, manufacturing process....

10.1002/jrs.1971 article EN Journal of Raman Spectroscopy 2008-04-04

The development and acquisition of a new class military systems known as Nano Air Vehicle (NAV) is possible in not too distant future result technological progress number areas. These vehicles will likely use flapping wings there strong evidence that for very small craft, flapping-wing performance superior to other options due dynamic effects create much higher average lift at low Reynolds numbers. An essential step towards engineering realization flight the understanding issues fully 3-D...

10.2514/6.2008-6396 article EN 35th AIAA Applied Aerodynamics Conference 2008-06-14

This paper deals with dynamic simulation and optimization of wastewater treatment plants. Moreover, the benchmark plant (www.benchmarkWWTP.org) was considered its corresponding model used. Simulations were carried out using gProms software for dry, rain storm weather data files. The consisted in determination continuous aeration internal recycle profiles which minimize energy under effluent constraints. results obtained showed that we able to save up 30% compared usual policy constraints are...

10.1109/pc.2013.6581445 preprint EN 2013-06-01

This paper deals with geometric shape optimization of a parallelepiped shaped fixed-bed reactor single phase liquid flow where chemical reaction takes place. The packing is sort static mixer made up solid cylindrical obstacles uniformly distributed in the reactor. reactive described by means momentum and mass transport equations laminar regime. objective to determine that maximizes conversion rate subjected some specified manufacturing constraints. approach developed based on adjoint system...

10.1137/20m1343841 article EN SIAM Journal on Applied Mathematics 2021-01-01

A series of supersonic wind tunnel tests was performed in the DREV 0.6 m x indraft facility order to obtain experimental data on snrface static pressure distribution and aerodynamic coefficients for projectiles during sabot separation. Two model variants were used: a full scale C-76 ArmourPiercing Fin-Stabilized Discarding-Sabot (AFFSDS) projectile generic APFSDS model. Relative attitudes locations sabot/projectile system frozen test section providing twelve configurations each variant The...

10.2514/6.1996-193 article EN 38th Aerospace Sciences Meeting and Exhibit 1996-01-15
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