Similarly shaped airfoils to NACA67A410
New! Bulk download of polars in Excel format: NACA67A410.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. NACA67-410 a=0.6
3. NACA66A410
4. NACA66-410 a=0.8
5. NACA66-510
6. NACA67-410 a=0.5
7. NACA66A411
8. NACA66-411 a=0.8
9. NACA67A411
10. NACA67-411 a=0.8
11. NACA67A409
12. NACA67-409 a=0.8
13. NACA66-410 a=0.6
14. NACA66-511
15. NACA65A410
16. NACA66-410
17. NACA65A411
18. NACA67-310 a=0.6
19. NACA67-310 a=0.8
20. NACA66-411 a=0.6
21. NACA66-410 a=0.5