Similarly shaped airfoils to NACA66-209
New! Bulk download of polars in Excel format: NACA66-209.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. NACA66-209 a=0.8
3. NACA65A209
4. NACA66-209 a=0.6
5. NACA67-209
6. NACA66-209 a=0.0
7. NACA66-209 a=0.5
8. NACA66-209 a=0.2
9. NACA65-209
10. NACA67A209
11. NACA67-209 a=0.8
12. EPPLER 904
13. NACA66-109 a=0.6
14. NACA66-109 a=0.8
15. NACA66A109
16. NACA66-109 a=0.5
17. NACA65-209 a=0.8
18. NACA67-209 a=0.6
19. NACA64A209
20. NACA67-209 a=0.5
21. NACA67-209 a=0.0