shock-expansion-airfoillisted

# Shock-Expansion Airfoil (aerodynamics/high-speed/shock-expansion-airfoil) Use when you must compute the supersonic pressure solution over a diamond (double-wedge) airfoil section by shock-expansion theory: oblique-shock relations handle the compression turns and Prandtl-Meyer fans handle the expansion turns on each planar surface, the surface states are marched turn by turn, and the panel pressures are integrated into section lift, wave drag, and leading-edge moment coefficients. This leaf implements the theta-beta-M relation (weak solution), the oblique-shock jump ratios, and the Prandtl-Meyer function internally in pure Python, stdlib only, so no sibling-leaf import is needed. It pairs with aerodynamics/high-speed/oblique-shock and aerodynamics/high-speed/prandtl-meyer for the local single-turn relations this leaf patches, with aerodynamics/high-speed/wave-drag-area-rule for the volume contribution to wave drag, and with aerodynamics/high-speed/swept-wing-aerodynamics for three-dimensional sweep effects. ## Domain quick reference - Diamond geometry: symmetric double wedge with semi-wedge half-angle eps on chord c. Four planar panels, each projecting c/2 on the chord: upper front and upper rear at +eps and -eps to the chord, lower front and lower rear at -eps and +eps. Leading-edge included angle is 2*eps. - Sign conventions: angles in degrees; positive alpha means the freestream comes from below the chord (nose-up, lower surface windward). A positive def