high-lift-systemslisted

Use when the task is high-lift device selection, flap clmax estimation, slat contribution, wing CLmax, or stall speed with flaps. Estimate high-lift system performance for conceptual design: compute the section clmax increment for trailing-edge flaps (plain, split, slotted, Fowler) and leading-edge devices (slat, Krueger), scale the increment with deflection, flap chord ratio, and flapped span fraction, combine flap and slat increments by superposition, apply the three-dimensional and sweep reduction to get wing CLmax, and derive the resulting stall speed. Produces the wing maximum lift coefficient, stall speed, drag increment, and pitching moment increment that size the flap schedule and drive field performance estimates. Trigger: high-lift, flap, slat, Fowler, Krueger, clmax, stall speed, lift increment.
ashfordeOU/aero-agent-skills · ★ 0 · AI & Automation · score 78

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

# High-Lift Systems (aerodynamics/high-lift/high-lift-systems) Use when the task is high-lift device selection and performance: flap and slat clmax increments, wing maximum lift coefficient, and the stall speed that results. ## Domain quick reference - Trailing-edge flaps raise the section clmax by an increment that depends on flap type, deflection, flap chord ratio, and flapped span fraction. Reference increments at full deflection and a flap chord ratio near 0.25 (widely cited textbook estimates, Raymer Aircraft Design: A Conceptual Approach, DATCOM-style scaling): Delta clmax = Delta clmax_ref * K_delta * K_chord * K_span K_delta = sin(delta) / sin(delta_max), clamped at delta_max K_chord = (c_f / c) / (c_f / c)_ref K_span = flapped span fraction - Typical section clmax increments at full deflection (chord ratio near 0.25, full span): plain 0.9, split 0.9, slotted 1.3, Fowler 1.6. A Fowler flap extends the chord, adding extension chord as c_f = c_f_base + extension_frac * c. - Leading-edge devices add a further increment: a full-span slat about 0.4, a partial-span slat scaled by span fraction, a Krueger flap about 0.3. - Wing-level CLmax applies a three-dimensional and sweep reduction: CLmax_wing = 0.9 * clmax_section * cos(Lambda) with the sweep angle Lambda in degrees. - Stall speed: V_stall = sqrt(2 * W / (rho * S * CLmax_wing)), with weight W in N, area S in m^2, and rho in kg/m^3. - Drag increment: Delta CD0 = CD0_ref * sin(delta)