Oblique Shock Wave Theory
For a given Mach number, M1, and corner angle, θ, the oblique shock angle, β, and the downstream Mach number, M2, can be calculated. M2 is always less than M1. Unlike after a normal shock, M2 can still be supersonic (weak shock wave) or subsonic (strong shock wave). Weak solutions are often observed in flow geometries open to atmosphere (such as on the outside of a flight vehicle). Strong solution may be observed in confined geometries (such as inside a nozzle intake). Strong solution is required when the flow need to match the downstream high pressure condition. Discontinuous changes also occur in the pressure, density and temperature, which all rise downstream of the oblique shock wave.
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—Thomas Nagel (b. 1938)