Similarly shaped airfoils to NACA67A412
New! Bulk download of polars in Excel format: NACA67A412.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. NACA67-412 a=0.6
3. NACA66A412
4. NACA67-412 a=0.5
5. NACA66-412 a=0.8
6. NACA66-512
7. NACA67-413 a=0.8
8. NACA67A413
9. NACA67A411
10. NACA67-411 a=0.8
11. NACA66A413
12. NACA66-413 a=0.8
13. NACA66-513
14. NACA66-412 a=0.6
15. NACA67-312 a=0.8
16. NACA67-312 a=0.6
17. NACA67-413 a=0.6
18. NACA66-412
19. NACA67-411 a=0.6
20. NACA67A512
21. NACA67A312