NACA66-218 a=0.2


New! Bulk download of polars in Excel format: NACA66-218%20a%3D0.2.xlsx


Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Dynamic plotter New!
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord

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Angle (deg),
positive is trailing edge down
DAT File
5NACA66-218 a=0.2FLAP5C40
15NACA66-218 a=0.2FLAP15C40
25NACA66-218 a=0.2FLAP25C40
35NACA66-218 a=0.2FLAP35C40
45NACA66-218 a=0.2FLAP45C40
-5NACA66-218 a=0.2FLAPM5C40
-15NACA66-218 a=0.2FLAPM15C40
-25NACA66-218 a=0.2FLAPM25C40
-35NACA66-218 a=0.2FLAPM35C40
-45NACA66-218 a=0.2FLAPM45C40