Similarly shaped airfoils to NACA67-410 a=0.6
New! Bulk download of polars in Excel format: NACA67-410%20a%3D0.6.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA67-410 a=0.8
3. NACA67A410
4. NACA66-410 a=0.6
5. NACA66-410 a=0.5
6. NACA66-411 a=0.6
7. NACA66-410 a=0.8
8. NACA66A410
9. NACA67-411 a=0.6
10. NACA67-409 a=0.6
11. NACA66-411 a=0.5
12. NACA67-409 a=0.5
13. NACA67-411 a=0.5
14. NACA66-510
15. NACA66-411 a=0.8
16. NACA67-510 a=0.0
17. NACA66A411
18. NACA67-409 a=0.8
19. NACA67-411 a=0.8
20. NACA67A510
21. NACA67A409