Similarly shaped airfoils to NACA67-210
New! Bulk download of polars in Excel format: NACA67-210.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. NACA67-210 a=0.8
3. NACA67-210 a=0.6
4. NACA67-210 a=0.5
5. NACA67-210 a=0.0
6. NACA67-210 a=0.2
7. NACA66-210
8. NACA67-110 a=0.6
9. NACA67-110 a=0.8
10. NACA67A110
11. NACA67-110 a=0.5
12. NACA66A210
13. NACA66-210 a=0.8
14. NACA66-211
15. NACA66-210 a=0.6
16. NACA0010-34 a=0.8 c(li)=0.2
17. NACA67-211
18. NACA67-209
19. NACA66-210 a=0.0
20. NACA66-210 a=0.5
21. NACA66-210 a=0.2