lift-curve-slopelisted

# Lift Curve Slope Estimation (aerodynamics/drag-polars/lift-curve-slope) Use when the task is wing lift curve slope estimation from section data: thin-airfoil theory for the section slope, lifting-line theory for the finite wing, simple sweep theory, the Prandtl-Glauert Mach correction, and lift coefficient from angle of attack. ## Domain quick reference - Section slope: thin-airfoil theory gives a0 = 2 * pi per radian for a flat plate or thin uncambered section; use a measured or computed value when one is available. Camber shifts the zero-lift angle, it does not change the thin-airfoil slope. - Finite wing (lifting-line theory, span efficiency e): a = a0 / (1 + a0 / (pi * e * AR)). With a0 = 2 * pi and e = 1 (elliptic loading) this reduces to a = a0 * AR / (AR + 2). - Sweep (simple sweep theory): a_swept = a * cos(sweep), sweep in degrees, documented range 0 <= sweep < 90 where cos(sweep) > 0. - Mach (Prandtl-Glauert): a_mach = a / sqrt(1 - M^2), documented range 0 <= M < 0.7. The correction is a subsonic small-disturbance result and becomes invalid as transonic effects appear above 0.7. - Combined order: section slope, then finite wing, then sweep, then Mach. Each step consumes the slope produced by the previous step. - Lift coefficient: C_L = a * (alpha - alpha_zero), alpha and alpha_zero in degrees, a per radian. The optional stall guard flags angles whose linear prediction exceeds the stall limit. - Validation anchor: NACA Report 824 (public do