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ashfordeOU (@ashfordeou) published this skill. Their other Agent Skills are listed on their SkillMD profile.

High Lift Systems by ashfordeou — Agent Skill

Name: High Lift Systems
Author: ashfordeOU

High Lift Systems

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 Updated Sep 17, 2026

File contents

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) / sin(delta_max), plus the induced-drag rise Delta CDi = Delta CL^2 / (pi * AR * e).
Pitching moment increment: Delta Cm = -Delta CL * (x_cp - x_ac) with the flap center-of-pressure and the wing aerodynamic center as fractions of chord.

Workflow

Select the flap type and the maximum deflection; get the reference increment and scaling constants with flap_clmax_increment.
For Fowler flaps, extend the chord with fowler_chord_ratio when the extension is known.
Add leading-edge device increments with slat_clmax_increment and combine with combined_clmax_increment (superposition).
Convert the section clmax to the wing value with wing_clmax using the sweep angle.
Compute the stall speed with stall_speed; estimate the drag and pitching moment increments with flap_drag_increment and flap_pitch_moment_increment.

Pitfalls

Mixing section and wing values: the 0.9 factor and the sweep cosine reduction apply once, at the wing level, not per device.
Using full-span reference increments for partial-span flaps: scale by the flapped span fraction first.
Forgetting the deflection clamp: beyond delta_max the increment stops growing (K_delta clamps at 1).
Treating a Krueger flap as a slat: increments differ (about 0.3 vs 0.4 at full span), and the scaling rules are separate.
Using stall speed with the clean CLmax: the whole point of the high-lift system is the flapped CLmax.

Behavior contract (gate 3)

The high-lift logic is exercised by the gate 3 contract test: scripts/test_high_lift_systems.py against scripts/high_lift_systems_logic.py (stdlib unittest, offline). Run: python3 scripts/test_high_lift_systems.py

Compliance

The flap and slat increment values are widely cited textbook estimates (Raymer, Aircraft Design: A Conceptual Approach), paraphrased here. FAR-25 and CS-25 are cited as reference only for the stall and field performance context; no proprietary or copyrighted text is reproduced.
compliance: STANDARDS-REF, gated: false.

---name: high-lift-systemsdescription: 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.license: Apache-2.0---# High-Lift Systems (aerodynamics/high-lift/high-lift-systems)Use when the task is high-lift device selection and performance: flapand slat clmax increments, wing maximum lift coefficient, and thestall 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) / sin(delta_max), plus the induced-drag rise Delta CDi = Delta CL^2 / (pi * AR * e).- Pitching moment increment: Delta Cm = -Delta CL * (x_cp - x_ac) with the flap center-of-pressure and the wing aerodynamic center as fractions of chord.## Workflow1. Select the flap type and the maximum deflection; get the reference increment and scaling constants with flap_clmax_increment.2. For Fowler flaps, extend the chord with fowler_chord_ratio when the extension is known.3. Add leading-edge device increments with slat_clmax_increment and combine with combined_clmax_increment (superposition).4. Convert the section clmax to the wing value with wing_clmax using the sweep angle.5. Compute the stall speed with stall_speed; estimate the drag and pitching moment increments with flap_drag_increment and flap_pitch_moment_increment.## Pitfalls- Mixing section and wing values: the 0.9 factor and the sweep cosine reduction apply once, at the wing level, not per device.- Using full-span reference increments for partial-span flaps: scale by the flapped span fraction first.- Forgetting the deflection clamp: beyond delta_max the increment stops growing (K_delta clamps at 1).- Treating a Krueger flap as a slat: increments differ (about 0.3 vs 0.4 at full span), and the scaling rules are separate.- Using stall speed with the clean CLmax: the whole point of the high-lift system is the flapped CLmax.## Behavior contract (gate 3)The high-lift logic is exercised by the gate 3 contract test:scripts/test_high_lift_systems.py againstscripts/high_lift_systems_logic.py (stdlib unittest, offline).Run:python3 scripts/test_high_lift_systems.py## Compliance- The flap and slat increment values are widely cited textbook estimates (Raymer, Aircraft Design: A Conceptual Approach), paraphrased here. FAR-25 and CS-25 are cited as reference only for the stall and field performance context; no proprietary or copyrighted text is reproduced.- compliance: STANDARDS-REF, gated: false.

Frequently asked questions