Similarly shaped airfoils to NACA66-611 a=0.2
New! Bulk download of polars in Excel format: NACA66-611%20a%3D0.2.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. NACA66-611 a=0.0
3. NACA67-611 a=0.2
4. NACA65-611 a=0.2
5. NACA67-711 a=0.0
6. NACA67-610 a=0.2
7. NACA66-612 a=0.2
8. NACA66-610 a=0.2
9. NACA66-511 a=0.5
10. NACA67-611 a=0.0
11. NACA66-712 a=0.0
12. NACA65-612 a=0.2
13. NACA65-711 a=0.0
14. NACA66-610 a=0.0
15. NACA67-610 a=0.0
16. NACA65-611 a=0.0
17. NACA67-710 a=0.0
18. NACA65-712 a=0.0
19. NACA66-710 a=0.0
20. NACA66-711 a=0.2
21. NACA66-511 a=0.2