Editing Shock wave (section)

=== Recompression shock ===
[[Image:Transonic flow patterns.svg|thumb|right|Recompression shock on a transonic-flow airfoil, at and above [[critical Mach number]] ]]
* These shocks appear when the flow over a transonic body is decelerated to subsonic speeds.
* Examples: Transonic wings, turbines
* Where the flow over the suction side of a transonic wing is accelerated to a supersonic speed, the resulting re-compression can be by either Prandtl–Meyer compression or by the formation of a normal shock. This shock is of particular interest to makers of transonic devices because it can cause separation of the boundary layer at the point where it touches the transonic profile. This can then lead to full separation and stall on the profile, higher drag, or shock-buffet, a condition where the separation and the shock interact in a resonance condition, causing resonating loads on the underlying structure.