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。
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