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执行固定翼气动阻力分解计算。当需要从几何参数计算详细阻力清单时调用。
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Based on SOC occupation classification
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。
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。
Showing SKILL.md
| name | fixed_wing_aero_buildup_runbook |
| description | 执行固定翼气动阻力分解计算。当需要从几何参数计算详细阻力清单时调用。 |
| stage | class2_preliminary |
| code_module | aircraft_design/class2_preliminary/aero_drag_buildup.py |
| dependencies | ["fixed_wing_aero_buildup_spec"] |
fixed_wing_overall_sizing_runbook 在“收敛后的阶段 2–7 扩展分析”中自动执行（Stage2 Aero）。initial_guess.cd0 是否合理？如果不合理，哪一部分在贡献阻力？”aircraft_design/aero_drag_buildup.py
cd0 及 Fuselage/Wing/Horizontal Tail/Vertical Tail/Misc/Wave Drag 分解requirements.cruise_altitude_m、requirements.cruise_mach：巡航工况initial_guess.thickness_ratio、initial_guess.sweep_deg、initial_guess.aspect_ratio、initial_guess.taper_ratiogeometry_shape / geometry_detailed（最可追溯）fixed_wing_overall_sizing_runbookoutput/<project>_*/advanced_design_results_*.json：
stage2_aero.cd0、stage2_aero.cd0_breakdown、stage2_aero.wave_dragoutput/<project>_*/advanced_design_report.md：可读的阻力分解表cd0 明显过大：优先检查机身尺度（长度/直径）与 thickness_ratio