Similarly shaped airfoils to NACA67-511 a=0.6
New! Bulk download of polars in Excel format: NACA67-511%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. NACA67-511 a=0.8
3. NACA66-511 a=0.6
4. NACA67A511
5. NACA66-511 a=0.5
6. NACA67-611
7. NACA67-512 a=0.6
8. NACA67-510 a=0.6
9. NACA66-512 a=0.6
10. NACA67-510 a=0.5
11. NACA66-512 a=0.5
12. NACA67-512 a=0.5
13. NACA66-511 a=0.8
14. NACA66A511
15. NACA67A611
16. NACA67-711
17. NACA66-512 a=0.8
18. NACA67-510 a=0.8
19. NACA66-611
20. NACA67-512 a=0.8
21. NACA67A510