CERFACS CERFACS Scientific Activity Report Jan. 2010 – Dec. 2011

TABLE DES FIGURES
3.6 LES results with elsA in NASA rotor 37 : (a) Instantaneous flow field shaded with the
density gradient and (b) comparison of efficiency curves (grid 1 : 10M cells, grid 2 : 25M
cells, grid 3 : 100M cells). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 152
3.7 Application of LES to the MUR235 test case : (a) instantaneous flow field colored by density
gradient gradρ/ρ (mark 1 is related to the normal shock and mark 2 to vortices produced
by the impact of freestream turbulence) and (b) wall heat transfer coefficient predicted with
structured (elsA) and unstructured (AVBP) flow solvers. . . . . . . . . . . . . . . . . . . . 154
3.8 Comparison of PIV measurements (up) with LES predictions (down) in a ribbed channel
configuration. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 155
4.1 LES with wall modeling on supersonic plane channel flow compared to Coleman DNS :
Mach = 1.5 (bottom) and Mach = 3 (top). . . . . . . . . . . . . . . . . . . . . . . . . . . 157
4.2 Jet in cross flow : embedded LES simulation. . . . . . . . . . . . . . . . . . . . . . . . . 158
4.3 Pressure coefficient field with incidence effect . . . . . . . . . . . . . . . . . . . . . . . . 160
4.4 Fan/Nacelle Configuration (axial momentum and blade pressure) . . . . . . . . . . . . . . 161
4.5 Coupled simulation between LES (AVBP solver) and the scoop temperature field (AVTP
solver). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161
4.6 Noise computation of a subsonic jet. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 162
4.7 Airfoil turbulence interaction noise. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 163
4.8 3D LES simulation of a rod-airfoil interaction. Comparison with experiment. . . . . . . . 163
7 Aviation and Environment 177
2.1 Left : minimum static pressure coefficient along the vortex centreline. Right : instantaneous
crossflow velocity field (colour) and particles location (dots). . . . . . . . . . . . . . . . . 181
2.2 Spatial distribution of ice crystals for different atmospheric situations : from left to right :
no turbulence, mild turbulence and strong turbulence. . . . . . . . . . . . . . . . . . . . . 182
2.3 Large-eddy simulations of atmospheric turbulence at Kilometer scale : Snapshots of
potential temperature fluctuations (left) and spectra of turbulent kinetic energy (right) . . . 183
2.4 Computational domain (left) and Mach number in a longitudinal cut (right) . . . . . . . . 184
2.5 Time evolution of the ozone content after an Titan 4 launch at 15 et 40 km. . . . . . . . . . 186
3.1 Distribution of the concentration of HOCl computed by the reduced model . . . . . . . . 188
3.2 Evolution of a Gaussian concentration advected by vortex centred at the equator. Left :
initial state, middle : after 600 iterations, right : after 1000 iterations. . . . . . . . . . . . . 189
3.3 Reduction in the ozone formation due to the use of alternate fuels at the 2026 horizon . . . 190
xii Jan. 2010 – Dec. 2011