Similarly shaped airfoils to NACA63-212
New! Bulk download of polars in Excel format: NACA63-212.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (13) | 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(1)-212
3. NACA63-212 a=0.8
4. HQ 1.0/12
5. NACA64-212 a=0.8
6. NACA63-212 a=0.6
7. NACA63-212 a=0.5
8. NACA63-212 a=0.0
9. NACA63-212 a=0.2
10. NACA64-212 a=0.6
11. NACA64-212 a=0.5
12. NACA64-212 a=0.0
13. NACA64-212 a=0.2
14. NACA63-112 a=0.6
15. NACA63-112 a=0.8
16. NACA63-112 a=0.5
17. NACA64-112 a=0.6
18. NACA64-112 a=0.8
19. NACA63A212
20. NACA64(1)-112
21. NACA64-112 a=0.5