delta-wing-vortex-liftlisted

# Delta Wing Vortex Lift (aerodynamics/cfd/delta-wing-vortex-lift) Use when the task is the separated-flow lift of a sharp-edged slender delta wing: the Polhamus leading-edge suction analogy (NASA TN D-3767, 1966) that adds a leading-edge-separation vortex term to the attached potential term. The leaf is the only separated-flow vortex-lift model in the library; it covers the regime the attached-flow siblings exclude. It pairs with aerodynamics/cfd/vortex-lattice-method, which owns the horseshoe-vortex attached-flow linear range, and with aerodynamics/high-lift/high-lift-systems for the mechanical-device alternatives. Valid for sharp leading edges, subsonic flow, aspect ratio about 0.5 to 2.0, alpha up to about 25 degrees. Does not model vortex breakdown onset (empirical charts only, not modeled), circulation control, blown flaps, or ice accretion. ## Domain quick reference - Aspect ratio of a full delta: AR = 4 / tan(Lambda_LE); 76 deg sweep gives about 1.0 and 45 deg gives 4.0. - Total lift (TN eq. 15): CL = Kp sin(a) cos^2(a) + Kv cos(a) sin^2(a), the sum of the potential term and the vortex term. - Potential term: CL_pot = Kp sin(a) cos^2(a), with the slender-wing small-angle slope Kp = pi * AR / 2. - Vortex term: CL_vort = Kv cos(a) sin^2(a), where Kv is the leading edge suction force coefficient, linear from 3.14 at AR 0 to 3.45 at AR 4 (clamped beyond 4). - Drag due to lift: CD_i = CL * tan(a), the product of the total lift coefficient and the tangent of