Similarly shaped airfoils to NACA64-109
New! Bulk download of polars in Excel format: NACA64-109.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. NACA64-109 a=0.8
3. NACA64-109 a=0.6
4. NACA63-109 a=0.8
5. NACA64-109 a=0.5
6. NACA64-109 a=0.0
7. NACA64-109 a=0.2
8. NACA63-109 a=0.6
9. NACA63-109 a=0.5
10. NACA63-109 a=0.0
11. NACA63-109 a=0.2
12. NACA63A109
13. NACA65-109
14. NACA64A109
15. NACA65-109 a=0.8
16. NACA65-109 a=0.6
17. NACA65-109 a=0.5
18. NACA65-109 a=0.0
19. NACA65-109 a=0.2
20. SC17s
21. SC17