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执行固定翼气动一级模型（CD0/e/k、巡航L/D）。当总体闭环需要气动输入或要诊断航程/爬升受阻时调用。
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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。
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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| name | fixed_wing_aero_runbook |
| description | 执行固定翼气动一级模型（CD0/e/k、巡航L/D）。当总体闭环需要气动输入或要诊断航程/爬升受阻时调用。 |
| stage | class2_preliminary |
| code_module | aircraft_design/class2_preliminary/aero_drag_buildup.py |
| dependencies | ["fixed_wing_aero_spec"] |
fixed_wing_overall_sizing_runbook 闭环驱动，不建议作为独立入口。CD = CD0 + k * CL^2k 由 AR 与 e 得到（一级估算）CL，进而估算巡航 L/Dinitial_guess.cd0、initial_guess.oswald_e、initial_guess.aspect_ratio。design_data.json 与 design_report_v2.md。cd0、e/AR、还是推进耗油模型导致的。cd0 过大通常直接损害航程与爬升：优先检查外形阻力与构型增量假设e 偏低会显著增大诱导阻力：优先检查 AR、翼尖与布局干扰cl_max 决定失速约束上界：与高升力装置策略联动调整