Similarly shaped airfoils to NACA64-221
New! Bulk download of polars in Excel format: NACA64-221.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(4)-221
3. NACA64-220
4. NACA63(4)-221
5. NACA64-220 a=0.8
6. NACA63-220
7. NACA64-220 a=0.6
8. NACA64-120 a=0.8
9. NACA64-120 a=0.6
10. NACA64-220 a=0.5
11. NACA64-120 a=0.5
12. NACA64-220 a=0.2
13. NACA63-220 a=0.8
14. NACA64-220 a=0.0
15. NACA63-120 a=0.8
16. NACA63-120 a=0.6
17. NACA63A220
18. NACA65-221
19. NACA64-120
20. NACA63-120 a=0.5
21. NACA63-220 a=0.6