Similarly shaped airfoils to NACA64(1)-212
New! Bulk download of polars in Excel format: n64212.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. NACA64-212
3. NACA63-212 a=0.8
4. NACA63-212
5. NACA64-212 a=0.6
6. HQ 1.0/12
7. NACA64-212 a=0.5
8. NACA63-212 a=0.6
9. NACA63A212
10. NACA63-212 a=0.5
11. NACA65(1)-212
12. NACA65-212 a=0.8
13. NACA65-212
14. NACA64A212
15. NACA64-312
16. NACA64-212 a=0.2
17. NACA63-312
18. NACA63-212 a=0.2
19. NACA64-212 a=0.0
20. NACA65-212 a=0.6
21. NACA63A211