ackeret-linearized-supersoniclisted

# Ackeret Linearized Supersonic (aerodynamics/high-speed/ackeret-linearized-supersonic) Use when you must compute the section coefficients of a thin airfoil at supersonic Mach by ackeret linearized supersonic theory (Liepmann and Roshko ch. 10, Anderson sec. 9): the ackeret parameter, the linearized surface pressure law, and the section lift, wave drag and leading edge moment of the flat plate, the thin biconvex circular-arc section and a cambered thin plate. The leaf integrates the linearized pressure coefficient over the surface slopes by deterministic Simpson quadrature and exposes the closed forms of the canonical thin sections, in pure stdlib Python. It pairs with the exact-march sibling aerodynamics/high-speed/shock-expansion-airfoil, whose diamond double-wedge march is the exact answer this leaf's linear values cross-check within 10%, and with the area-Mach duct relations of aerodynamics/high-speed/isentropic-flow-relations. ## Domain quick reference - Ackeret parameter: beta = sqrt(M^2 - 1), the divisor of every linear supersonic coefficient. beta -> 0 as M -> 1 (the coefficients diverge, hence the M <= 1 guard) and beta -> M at large M. All angles are RADIANS; positive alpha means the freestream sits above the chord, so the lower surface is windward. - Linearized surface pressure law: on a surface deflected by theta from the freestream (theta positive compresses, Cp positive windward), Cp = +-2*theta/beta. Upper surface cp_u = 2*(phi_u - alpha)/beta,