Similarly shaped airfoils to NACA67-612
New! Bulk download of polars in Excel format: NACA67-612.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. NACA67-512 a=0.8
3. NACA66-612
4. NACA66A512
5. NACA67-512 a=0.6
6. NACA66-512 a=0.8
7. NACA67-613
8. NACA67-611
9. NACA67A511
10. NACA67-712
11. NACA66-613
12. NACA67A513
13. NACA67-511 a=0.8
14. NACA67-513 a=0.8
15. NACA66A513
16. NACA66-513 a=0.8
17. NACA67-412 a=0.8
18. NACA67A612
19. NACA67-512 a=0.5
20. NACA67A412
21. NACA67-412 a=0.6