Fig. 1: Unsteady Flow Simulation in a Multistage High Pressure Compressor
Date: 2008
Author(s): Nicolas Gourdain and Marc Montagnac
Credit: SNECMA, ONERA and CERFACS

Fig. 2: Simulation of a Passive Blade Control Device in an Axial Compressor
Date: 2007
Author(s): Nicolas Gourdain
Credit: SNECMA, ONERA and CERFACS

Fig. 3: Simulation of the Flow in the Transonic Compressor Nasa Rotor 37
Date: 2007
Author(s): Nicolas Gourdain
Credit: NASA, ONERA and CERFACS

Fig. 4: Numerical Simulation of a Casing Treatment Solution in an Axial Compressor
Date: 2007
Author(s): Nicolas Gourdain and Marc Montagnac
Credit: SNECMA, ONERA and CERFACS
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Fig. 5: Wake vortices generated by a civil aircraft
Date: 1974
Author(s): NASA photo
Credit: NASA

Fig. 6: Streamlines from wing and flap tips
Date: 2000
Author(s): A. Benkenida and G. Jonville
Credit: CERFACS (Project C-WAKE)
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Fig. 7: LES of the near wake of a civil aircraft type, isolevel of instantaneous vorticity magnitude
Date: 2000
Author(s): F. Laporte
Credit: CERFACS
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Fig. 8: LES of vortex pair (b_0/r_c=6) for wake turbulence (v_rms/V_0=1%), development of the instability followed by the onset of the Crow instability
Date: 2000
Author(s): H. Moët
Credit: CERFACS (Project S-WAKE)
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Fig. 9: Secondary vortex experiencing the elliptic instability
Date: 2000
Author(s): F. Laporte and H. Moët
Credit: CERFACS (Project C-WAKE)
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Fig. 10: Linear phase of the development of the short-wavelength elliptic mode in a low circulation-based Reynolds number, three isosurfaces of vorticity magnitude
Date: 2000
Author(s): F. Laporte
Credit: CERFACS
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Fig. 11: Saturation of the elliptic mode and formation of transverse vortex pairs
Date: 2000
Author(s): F. Laporte
Credit: CERFACS
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Fig. 12: Multiblock mesh around the aircraft model
Date: 2000
Author(s): R. Struijs and G. Jonville
Credit: CERFACS (Project WAVENC)
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Fig. 13: NSMB, isoMach field on the skin of a high speed propeller with incidence
Date: 2002
Author(s): X. Escrivá and G. Grondin
Credit: CERFACS and Airbus France (Project OCMATH)
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Fig. 14: NSMB, turbofan rotor 3D mesh (only one passage is used for numerical simulations)
Date: 2002
Author(s): L. Kozuch and D. Darracq
Credit: CERFACS, Lab. de Mec. des Fluides et d'Acoustique, École Centrale de Lyon and LTS
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Fig. 15: NSMB, Turbomachinery Flows
Date: 2001
Author(s): L. Kozuch and D. Darracq
Credit: CERFACS, Liebherr-Aerospace Toulouse (LTS) and Technofan
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Fig. 16: NSMB, Euler flow simulation around the HSP propeller, M=0.7
Date: 2000
Author(s): G. Grondin, X. Escrivá and D. Darracq
Credit: CERFACS, Ratier-Figeac and Airbus France
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Fig. 17: NSMB, X component of the velocity and streamlines starting from the inlet
Date: 2000
Author(s): T. Soulères and F. Ducros
Credit: CERFACS and PSA
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Fig. 18: NSMB, vortex structure around a missile at high angle of attack
Date: 2000
Author(s): J. Cormier
Credit: CERFACS and EADS Missiles

Fig. 19: NSMB, steady pitching maneuver
Date: 2000
Author(s): S. Champagneux
Credit: CERFACS and Airbus France
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Fig. 20: NSMB, supersonic tongue in static movement (top) and in yawing movement (bottom)
Date: 2000
Author(s): J. Cormier and S. Champagneux
Credit: CERFACS and Airbus France
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Fig. 21: NSMB, Mach number computed with automatic differentiation applied to the radius in a blade to blade cut
Date: 2000
Author(s): G. Jonville, L. Kozuch and A. Corjon
Credit: CERFACS (Project OPTI-BLADE)

Fig. 22: elsA, pressure distribution around the a [wing+pylon+nacelle] configuration with running engine in transonic flow regime
Date: 2000
Author(s): S. Champagneux
Credit: CERFACS, ONERA and Airbus France
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Fig. 23: NSMB, LES of the flow around the A-profile
Date: 1999
Author(s): B. Caruelle and F. Ducros
Credit: CERFACS and Airbus France (Project EEC LESFOIL)
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Fig. 24: NSMB, topology of the flow around a nacelle in a crosswind preconditioning for low Mach number flows
Date: 1999
Author(s): S. Champagneux
Credit: CERFACS and Airbus France

Fig. 25: NSMB, perfect gas hypersonic flow around a re-entry capsule (ARD): skin friction lines
Date: 2000
Author(s): S. Champagneux
Credit: CERFACS and EADS Launch Vehicles
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Fig. 26: NSMB, NACA640010 flutter calculation (Mach=0.89, V*=2.2)
Date: 2000
Author(s): J. Bohbot and D. Darracq
Credit: CERFACS
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Fig. 27: NSMB, flutter calculation response
Date: 2000
Author(s): J. Bohbot and D. Darracq
Credit: CERFACS
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Fig. 28: elsA/AMR technique applied to the AS28G airfoil: mach contour lines
Date: 2001/02
Author(s): J.C. Jouhaud, M. Montagnac
Credit: CERFACS, ONERA and Airbus France
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Fig. 29: elsA/AMR technique applied to the AS28G airfoil: meshes
Date: 2001/02
Author(s): J.C. Jouhaud and M. Montagnac
Credit: CERFACS, ONERA and Airbus France
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Fig. 30: elsA/AMR technique applied to the AS28G airfoil: shock on the wing
Date: 2001/02
Author(s): J.C. Jouhaud and M. Montagnac
Credit: CERFACS, ONERA and Airbus France
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Fig. 31: elsA/Patched grid technique applied to the RAE2822 test case
Date: 2001
Author(s): M. Montagnac
Credit: CERFACS
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Fig. 32: NSMB/AMR technique applied to a NACA0012 airfoil: hierarchical grid structure
Date: 2001
Author(s): J.C. Jouhaud
Credit: CERFACS and Airbus France
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Fig. 33: NSMB/AMR technique with patched-grid applied to a NACA0012 airfoil: meshes and mach contour lines
Date: 2001
Author(s): J.C. Jouhaud
Credit: CERFACS and Airbus France
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Fig. 34: NSMB/AMR technique applied to wake vortex simulations: flow simulation behind a swim
Date: 2000
Author(s): J.C. Jouhaud
Credit: CERFACS and Airbus France
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Fig. 35: NSMB/AMR technique applied to wake vortex simulations: civil aircraft during the landing configuration
Date: 2000
Author(s): J.C. Jouhaud and A. Benkenida
Credit: CERFACS
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Fig. 36: NSMB/Patched-grid technique: S28G complex aircraft calculation (NS Baldwin-Lomax)
Date: 1999
Author(s): J. Bohbot and D. Darracq
Credit: CERFACS and Airbus France
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Fig. 37: NSMB/Patched-grid technique: M6 wing (NS Spalart-Allmaras)
Date: 1999
Author(s): J. Bohbot and D. Darracq
Credit: CERFACS and Airbus France
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Fig. 38: NSMB/Patched-grid technique: flow simulation around a fighter perturbed by the optronic system and the feeder
Date: 1999
Author(s): G. Jonville, J. Bohbot and D. Darracq
Credit: CERFACS and Thales
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