Similarly shaped airfoils to N-11


New! Bulk download of polars in Excel format: n11.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
Dynamic plotter New!
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.
1. USA-35B
2. I.S.A. 962
3. Eiffel 430 (Lachassgne)
4. I.S.A. 960
5. NACA45010.5
6. NACA45012
7. NACA63-612 a=0.0
8. NACA64-612 a=0.0
9. NACA63-611 a=0.0
10. M-451-12.0
11. NACA63-612 a=0.2
12. NACA64-611 a=0.0
13. NACA 8-H-12
14. NACA64-612 a=0.2
15. NACA35010.5
16. NACA45010
17. USA 45 M
18. NACA63-611 a=0.2
19. NACA63-512 a=0.2
20. NACA44010.5
21. NACA64-611 a=0.2