Similarly shaped airfoils to NACA64-611 a=0.6
New! Bulk download of polars in Excel format: NACA64-611%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
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2. NACA64-611 a=0.5
3. NACA63-611 a=0.5
4. NACA65-611 a=0.6
5. GA 37-611
6. NACA65-611 a=0.5
7. GA 35-611
8. GA 35A611
9. GA 40-611
10. GA 40A611
11. GA 37A611
12. NACA64-612 a=0.6
13. NACA64-610 a=0.6
14. NACA64-611 a=0.8
15. NACA65-610 a=0.6
16. NACA63-610 a=0.6
17. NACA63-612 a=0.6
18. S4158
19. NACA63-611 a=0.8
20. NACA64-610 a=0.5
21. NACA65-610 a=0.5