The problem considers the flow around an airfoil at an gle of attack   and a free stream Mach number of   (   ). The flow is transonic, and has a fairly strong shock near the mid-chord (   ) on the upper (suction) side. The chord length is 1 m.

external_compressible\airfoil-1.cas.gz
.....................\airfoil-1.dat.gz
.....................\airfoil-2.cas.gz
.....................\airfoil-2.dat.gz
.....................\airfoil.cas.gz
.....................\airfoil.dat.gz
.....................\airfoil.msh
.....................\cd-history
.....................\cl-history
.....................\cm-history
.....................\monitor-1.out
external_compressible

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