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固定翼气动方案设计：阻力分解、极曲线、升阻比与高升力装置取值范围。当需要建立可用于性能/重量闭合的气动模型时调用。
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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。
| name | fixed_wing_aero_spec |
| description | 固定翼气动方案设计：阻力分解、极曲线、升阻比与高升力装置取值范围。当需要建立可用于性能/重量闭合的气动模型时调用。 |
| stage | class2_preliminary |
| code_module | aircraft_design/class2_preliminary/aero_drag_buildup.py |
| dependencies | ["fixed_wing_overall_sizing_runbook"] |
CD = CD0 + k * CL^2CLmax 与阻力增量策略（后续细化）fixed_wing_overall_sizing_runbook 在 Class I 闭环与收敛后扩展阶段共同使用：
requirements.cruise_altitude_m、requirements.cruise_machinitial_guess.cd0、initial_guess.oswald_einitial_guess.aspect_ratioCLmax 假设支撑约束（后续可参数化）S, AR, b, cbarcd0, e, cl_maxcd0：零升阻系数k：诱导阻力系数（由 AR 与 e 给出）L/D：巡航点升阻比估算cl_max 与起降构型策略（需要满足失速/起降约束）