Similarly shaped airfoils to NACA64-511 a=0.6
New! Bulk download of polars in Excel format: NACA64-511%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
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2. NACA64-511 a=0.5
3. NACA63-511 a=0.5
4. GA 37-411
5. NACA65-511 a=0.6
6. GA 35-411
7. GA 35A411
8. NACA65-511 a=0.5
9. GA 40-411
10. GA 40A411
11. GA 37A411
12. NACA64-511 a=0.8
13. NACA63-511 a=0.8
14. K3311 (original)
15. K3311 (smoothed)
16. S4158
17. NACA64-512 a=0.6
18. NACA64-510 a=0.6
19. NACA65-510 a=0.6
20. NACA63-510 a=0.6
21. NACA63-512 a=0.6