How do I install the Airfoil Selection skill?

Run npx skillmds@latest add ashfordeou/airfoil-selection in your terminal (requires Node.js), paste this page's agent-chat prompt into Claude, Cursor, or any MCP-connected agent, or download the SKILL.md file and copy it into your agent's skills directory.

Is Airfoil Selection safe to use?

This skill has not completed SkillMD's automated safety review yet. SkillMD never runs a skill's scripts for you; review the SKILL.md before installing.

Which AI agents work with Airfoil Selection?

This skill is tagged as working with Claude Code, Claude.ai, OpenAI Codex. SKILL.md is an open format, so most agents that read a skills directory can load it too.

Is Airfoil Selection free to use?

Yes. Installing skills from SkillMD is free. This skill is licensed under Apache-2.

Who published Airfoil Selection?

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

Airfoil Selection by ashfordeou — Agent Skill

Name: Airfoil Selection
Author: ashfordeOU

Airfoil Selection

Use when you must select an airfoil section for a wing design: score candidate airfoils by lift-to-drag ratio at the design condition, filter them by minimum thickness, and choose the best qualified section from classic airfoil data. Produces the candidate scoring, the thickness filter verdict, and the selected airfoil identifier that feeds the wing layout. Trigger: airfoil selection, wing design, lift to drag ratio, thickness, naca airfoils, section selection.

ashfordeOU e8b38cc 3 files · 5.8 KB Updated Sep 17, 2026

File contents

Airfoil Section Selection (aerodynamics/airfoil/airfoil-selection)

Use when the task is airfoil section selection for a wing: scoring candidates by lift-to-drag ratio, filtering by thickness, and choosing the best qualified section.

Domain quick reference

Classic airfoil data (NACA Report 824 and successors) supplies lift and drag coefficients per section.
The design condition defines the target lift coefficient and Reynolds number.
Thickness constrains the section: structural depth and internal volume come from the thickness ratio.
Selection maximizes lift-to-drag ratio among sections that meet the minimum thickness.

Workflow

Collect candidate sections with cl, cd, and thickness at the design condition.
Score each with ld_ratio.
Filter with thickness_ok.
Select with select_airfoil.
Confirm the choice against the design lift condition.

Pitfalls

Choosing by cl alone instead of lift-to-drag ratio.
Ignoring the thickness constraint until the structure is sized.
Comparing candidates at different Reynolds numbers.

Behavior contract (gate 3)

The scoring, filtering, and selection logic is exercised by the gate 3 contract test: scripts/test_airfoil_selection.py against scripts/airfoil_selection_logic.py (stdlib unittest, offline). Run: python3 scripts/test_airfoil_selection.py

Compliance

NACA Report 824 is US government work (public domain); summary and physics values only, per standards-map.yaml.
compliance: STANDARDS-REF, gated: false.

---name: airfoil-selectiondescription: Use when you must select an airfoil section for a wing design: score candidate airfoils by lift-to-drag ratio at the design condition, filter them by minimum thickness, and choose the best qualified section from classic airfoil data. Produces the candidate scoring, the thickness filter verdict, and the selected airfoil identifier that feeds the wing layout. Trigger: airfoil selection, wing design, lift to drag ratio, thickness, naca airfoils, section selection.license: Apache-2.0---# Airfoil Section Selection (aerodynamics/airfoil/airfoil-selection)Use when the task is airfoil section selection for a wing: scoringcandidates by lift-to-drag ratio, filtering by thickness, andchoosing the best qualified section.## Domain quick reference- Classic airfoil data (NACA Report 824 and successors) supplies lift and drag coefficients per section.- The design condition defines the target lift coefficient and Reynolds number.- Thickness constrains the section: structural depth and internal volume come from the thickness ratio.- Selection maximizes lift-to-drag ratio among sections that meet the minimum thickness.## Workflow1. Collect candidate sections with cl, cd, and thickness at the design condition.2. Score each with ld_ratio.3. Filter with thickness_ok.4. Select with select_airfoil.5. Confirm the choice against the design lift condition.## Pitfalls- Choosing by cl alone instead of lift-to-drag ratio.- Ignoring the thickness constraint until the structure is sized.- Comparing candidates at different Reynolds numbers.## Behavior contract (gate 3)The scoring, filtering, and selection logic is exercised by thegate 3 contract test: scripts/test_airfoil_selection.py againstscripts/airfoil_selection_logic.py (stdlib unittest, offline).Run:python3 scripts/test_airfoil_selection.py## Compliance- NACA Report 824 is US government work (public domain); summary and physics values only, per standards-map.yaml.- compliance: STANDARDS-REF, gated: false.

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