Similarly shaped airfoils to NACA66A611
New! Bulk download of polars in Excel format: NACA66A611.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. NACA66-711
3. NACA65A611
4. NACA67A611
5. NACA67-611 a=0.8
6. NACA67-711
7. NACA65-611 a=0.8
8. NACA66A612
9. NACA66A610
10. NACA66-612 a=0.8
11. NACA67A610
12. NACA65A612
13. NACA67-610 a=0.8
14. NACA66-610 a=0.8
15. NACA66-611 a=0.6
16. NACA65-711
17. NACA66-710
18. NACA66-712
19. NACA67-710
20. NACA64A611
21. NACA65-612 a=0.8