Similarly shaped airfoils to NACA67-109 a=0.8
New! Bulk download of polars in Excel format: NACA67-109%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. NACA67-109 a=0.6
3. NACA67-109 a=0.5
4. NACA67-109
5. NACA67-109 a=0.2
6. NACA67-109 a=0.0
7. NACA66-109 a=0.8
8. NACA66A109
9. NACA66-109 a=0.6
10. NACA66-109
11. NACA66-109 a=0.5
12. NACA66-109 a=0.2
13. NACA66-109 a=0.0
14. NACA67-209
15. NACA66-110 a=0.8
16. NACA66A110
17. NACA66-110 a=0.6
18. NACA66-110 a=0.5
19. NACA66-110
20. NACA65A109
21. NACA67-209 a=0.0