Similarly shaped airfoils to NACA64-218
New! Bulk download of polars in Excel format: NACA64-218.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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. NACA63-218
3. NACA64-218 a=0.6
4. NACA64(3)-218
5. NACA64-218 a=0.5
6. NACA63-218 a=0.8
7. NACA64-218 a=0.2
8. NACA64-118 a=0.8
9. NACA64-118 a=0.6
10. NACA64-218 a=0.0
11. NACA64-118 a=0.5
12. NACA63-218 a=0.6
13. NACA63-218 a=0.5
14. NACA63(3)-218
15. NACA63-118 a=0.8
16. NACA63-118 a=0.6
17. NACA63-218 a=0.2
18. NACA63-218 a=0.0
19. NACA63-118 a=0.5
20. NACA64-219
21. NACA64-217