Aerodynamics:
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Ref.Area= 141.41747 m²
L/D     = 17.68342
CL      = 0.57000
CD      = 0.03223
CDfuse  = 0.00672
CDi     = 0.01117
CDwing  = 0.00817
CDhtail = 0.00255
CDvtail = 0.00172
CDnace  = 0.00189
CDBLIf  = -0.00000
CDBLIw  = -0.00000

Drag Areas = CD × Sref:
CL     × Sref = 80.60796 m²
CD     × Sref = 4.55839 m²
CDfuse × Sref = 0.95001 m²
CDi    × Sref = 1.57979 m²
CDwing × Sref = 1.15581 m²
CDhtail× Sref = 0.36105 m²
CDvtail× Sref = 0.24377 m²
CDnace × Sref = 0.26796 m²
CDBLIf × Sref = -0.00000 m²
CDBLIw × Sref = -0.00000 m²

