Editing Shock wave (section)

=== Attached shock ===
* These shocks appear as ''attached'' to the tip of sharp bodies moving at supersonic speeds.
* Examples: Supersonic wedges and cones with small apex angles.
* The attached shock wave is a classic structure in aerodynamics because, for a perfect gas and inviscid flow field, an analytic solution is available, such that the pressure ratio, temperature ratio, angle of the wedge and the downstream Mach number can all be calculated knowing the upstream Mach number and the shock angle. Smaller shock angles are associated with higher upstream Mach numbers, and the special case where the shock wave is at 90° to the oncoming flow (Normal shock), is associated with a Mach number of one. These follow the "weak-shock" solutions of the analytic equations.