Supersonic external flows


Figure 2 shows the density field for the computation of Mach 2 flow past a circular cylinder. The Reynolds number is 1000. Adaptive techniques are utilized to resolve the shock structures and the boundary/shear layers. One can observe a strong bow shock upstream of the cylinder and a weaker tail shock in the wake. The shock stand-off distance compares quite well with experimental observations.

 
M=2, Re=1000 flow
past a cylinder

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