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生成固定翼总体设计方案（需求→约束→设计点→初步尺寸→重量/性能闭合）。当需要给出固定翼总体方案、关键参数范围与决策依据时调用。
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npx skills add https://github.com/BaiSongt/aircraft-design-skill --skill fixed-wing-overall-sizing-specThe command stays on one line. Scroll horizontally to inspect it before copying.
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执行包含高级分析与机身几何的固定翼总体设计流程。初步分析收敛后调用，含高级分析、几何约束与机身外形。
固定翼总体设计唯一入口：执行 Class I 闭环并在收敛后进入阶段 2–7 扩展分析，落盘输出报告/数据/外形资产，并可选 PySide6 实时可视化。
执行固定翼约束校核并给出设计点调整建议。当用户关心起降/失速/巡航/爬升约束是否满足或要定位卡点时调用。
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Showing SKILL.md
| name | fixed_wing_overall_sizing_spec |
| description | 生成固定翼总体设计方案（需求→约束→设计点→初步尺寸→重量/性能闭合）。当需要给出固定翼总体方案、关键参数范围与决策依据时调用。 |
| stage | entry |
| code_module | aircraft_design/run_sizing.py, aircraft_design/class2_preliminary/fixed_wing_overall.py |
| dependencies | ["fixed_wing_overall_sizing_runbook","fixed_wing_weights_spec","fixed_wing_constraints_spec"] |
fixed_wing_overall_sizing_runbook 执行。requirements.*initial_guess.*geometry_shape、geometry_detailed、geometry_constraints、systemsrequirements：航程、载荷、巡航点、起降距离、过载/升限等initial_guess：thrust_to_weight、wing_loading_pa、aspect_ratio、sweep_deg、taper_ratio、thickness_ratio、sfc_cruise_1_s、cd0、oswald_e方案输出建议包含：
outputs.design_point.wing_loading_pa、outputs.design_point.thrust_to_weightoutputs.wing_area_m2、outputs.geometry.span_m、outputs.geometry.cbar_moutputs.aero.*（或收敛后扩展阶段的 stage2_aero.*）outputs.mtow_kg、outputs.empty_weight_kg、outputs.fuel_weight_kgoutputs.performance.*（或扩展阶段的 stage3_propulsion.*/stage4_mission.*）(W/S) <= q * CLmax