Similarly shaped airfoils to NACA64-220
New! Bulk download of polars in Excel format: NACA64-220.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. NACA63-220
3. NACA64-220 a=0.6
4. NACA64-220 a=0.5
5. NACA64-120 a=0.8
6. NACA64-120 a=0.6
7. NACA63-220 a=0.8
8. NACA64-220 a=0.2
9. NACA64-120 a=0.5
10. NACA64-220 a=0.0
11. NACA63-220 a=0.6
12. NACA63-120 a=0.8
13. NACA63-120 a=0.6
14. NACA63-220 a=0.5
15. NACA64-320
16. NACA63-220 a=0.2
17. NACA63-120 a=0.5
18. NACA64-120
19. NACA64-221
20. NACA64-219
21. NACA63-220 a=0.0