A flat plate at 6° and Mach 2.00: a shock below, a fan above

Each face of the section is a turn, and the pressure on it follows from the sequence of turns that reached it — a compression is an oblique shock, an expansion is a fan. Supersonic flow carries no information upstream, so each face can be solved in order with no inversion and no iteration. The pressure coefficients printed on the faces are the solved values.

5 essays call supersonic-section. The drawing above is what it returns with no arguments at all; every call below passes it something, because a placement that passes nothing draws whichever member of the family the generator happens to default to rather than the one its essay argues about.

It is also the blast radius. Changing supersonic-section changes every figure listed here at once, and on this site it may change what they assert as well as what they show — which is what has to be rebuilt and looked at before the change is believed.