Similarly shaped airfoils to NACA66-111 a=0.8
New! Bulk download of polars in Excel format: NACA66-111%20a%3D0.8.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
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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2. NACA66-111 a=0.6
3. NACA66-111 a=0.5
4. NACA66-111
5. NACA66-111 a=0.2
6. NACA66-111 a=0.0
7. NACA65A111
8. NACA66-211
9. NACA67-111 a=0.8
10. NACA67A111
11. NACA67-111 a=0.6
12. NACA67-111 a=0.5
13. NACA67-111
14. NACA67-111 a=0.2
15. NACA67-111 a=0.0
16. NACA65-111 a=0.8
17. NACA66-211 a=0.0
18. NACA65-111 a=0.6
19. NACA66-112 a=0.8
20. NACA66A112
21. NACA66A110