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The following figure shows the contours of temperature in the flowfield around
a blunt nose cone. The cone is supersonic, traveling at a Mach number
of 10.6. The shock wave around the cone is located at the outer edge
of the contours. These results were generated on Massively Parallel
computers and show the class of problems being solved on these
architectures. This solution is an example of the use of scalable, parallel
iterative methods.
The following figure depicts isocontour pictures of the translational
and vibrational temperature for a hypersonic five-species viscous
reacting air flow around a two-dimensional axisymmetric blunt body.
The flow is out of thermal equilibrium as the vibrational and
translational temperatures behind the shock differ drastically. This
benchmark solution calibrates computations for hypervelocity
projectile problems.
aal@cfdlab.ae.utexas.edu
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