Similarly shaped airfoils to NACA67-309 a=0.0
New! Bulk download of polars in Excel format: NACA67-309%20a%3D0.0.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. NACA66-309 a=0.0
3. NACA66-309 a=0.2
4. NACA67-209 a=0.5
5. NACA67-209 a=0.6
6. NACA67-209 a=0.2
7. NACA66-310 a=0.0
8. NACA67-309 a=0.5
9. NACA66-310 a=0.2
10. NACA66-209 a=0.5
11. NACA67-310 a=0.0
12. MH 24 9.01%
13. NACA67-310 a=0.2
14. EPPLER 904
15. NACA66-209 a=0.6
16. NACA67-409 a=0.0
17. NACA67-209 a=0.0
18. NACA66-209 a=0.2
19. NACA67-209 a=0.8
20. NACA67-309 a=0.6
21. NACA67A209