wing-planform-designlisted

Use when you must derive the wing-planform-design reference geometry and the spanwise loading of a straight-tapered wing from the span, the area, and the taper-ratio: compute the root-chord and the tip-chord, the mean-geometric-chord, the mean-aerodynamic-chord with its mac-span-station, and convert the leading-edge-sweep into the quarter-chord-sweep. Compute the spanwise-load-distribution with the schrenk-approximation to obtain the local-lift-coefficient at any station, and size the washout-angle so the root reaches stall before the tip, giving the stall-sequencing for a benign stall. Produces the reference chords, the sweep line, and the loading check that feed the lift-curve-slope and vortex-lattice-method leaves. Trigger: wing planform design, taper ratio, mean aerodynamic chord, MAC span station, quarter chord sweep, Schrenk approximation, spanwise load distribution, washout angle.
ashfordeOU/aero-agent-skills · ★ 0 · AI & Automation · score 78

Install: claude install-skill ashfordeOU/aero-agent-skills

# Wing Planform Design (aerodynamics/wing-design/wing-planform-design) Use when the task is the planform geometry and spanwise loading of a straight-tapered wing: the reference chords (root, tip, mean geometric, mean aerodynamic), the MAC spanwise station, the sweep reference-line conversion, the Schrenk spanwise load approximation, and the washout sizing for a root-first stall sequence. ## Domain quick reference - A straight-tapered (trapezoidal) wing is defined by the span b, the reference area S, and the taper ratio lambda = ct/cr in (0, 1]. The derived reference geometry is the aspect ratio AR = b^2/S, the root chord cr = 2S/(b(1+lambda)), the tip chord ct = lambda*cr, and the mean geometric chord cbar = S/b. Worked example, b = 35 m, S = 125 m^2, lambda = 0.3: AR = 9.8, cr = 5.4945 m, ct = 1.6484 m, cbar = 3.5714 m. - Mean aerodynamic chord: MAC = (2/3)cr(1+lambda+lambda^2)/(1+lambda). For the example: MAC = 3.9166 m. The MAC is the chord of the equivalent rectangular wing that preserves the pitch moment behavior; it is the reference for the center of gravity limits and the neutral point, not the mean geometric chord. - MAC spanwise station from the root: y_MAC = (b/6)(1+2lambda)/(1+lambda). For the example: y_MAC = 7.1795 m from the root centerline. Checks: rectangular wing (lambda = 1) gives y_MAC = b/4, a triangle (lambda toward 0) gives y_MAC = b/6. - Local chord at span station eta = 2y/b in [0, 1]: c(eta) = cr(1 - (1-lambda)eta), eta =