Similarly shaped airfoils to NACA64-311 a=0.6
New! Bulk download of polars in Excel format: NACA64-311%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. NACA63-311 a=0.6
3. NACA63-311 a=0.5
4. NACA64-311 a=0.8
5. NACA63-311 a=0.8
6. GA 37-211
7. NACA65-311 a=0.6
8. NACA64-411
9. NACA65-311 a=0.5
10. GA 35-211
11. NACA63-411
12. GA 35A211
13. NACA63A311
14. SB95 10.5/2
15. SD6060-104-88
16. GA 40-211
17. NACA65-311 a=0.8
18. GA 40A211
19. GA 37A211
20. NACA64A311
21. SB98 VM5 mid