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Fig. 1.
Downwind view and pressure contours showing the characteristic lambda
structure for the Onera M6 wing (left) and kiln flow temperature contours
Fig. 2.
Onera M6 wing: Strong scalability for both the Xeon Phi (left) and the hosts.
Ideal and measured scalabilities, parallel eciency and mean number of elements per
core are shown
Onera M6 Wing: Compressible Inviscid Flow, Explicit Scheme.
This is
compressible flow passing an Onera M6 wing, under the following conditions:
Mach 0.8395, Reynolds number 11.72E06, angle of attack 3.06 degrees and
angle of side-slip 0.0 degrees [8]. Flow is solved with an explicit scheme, with a
Preconditioned Variational Multiscale (P-VMS) scheme, presented in [7]. Figure
1 shows the pressure contour plot on the downstream surface of the wing. Figure
2 shows the strong scalability for the Xeon Phi. The mesh is made of 1.8M
tetrahedra, with four degrees of freedom per node (momentum vector, density
scalar and energy scalar).
