Similarly shaped airfoils to NACA63A112
New! Bulk download of polars in Excel format: NACA63A112.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. NACA64-112 a=0.8
3. NACA65-112 a=0.8
4. NACA64(1)-112
5. NACA64-112 a=0.6
6. NACA65-112 a=0.6
7. NACA65-112
8. NACA64-112
9. NACA64-112 a=0.5
10. NACA65-112 a=0.5
11. NACA65-112 a=0.2
12. NACA64-112 a=0.2
13. NACA65-112 a=0.0
14. NACA64-112 a=0.0
15. NACA63-112 a=0.8
16. NACA63-112 a=0.6
17. NACA63-112
18. R140 (original)
19. NPL 9626
20. NACA63-112 a=0.5
21. R140 12.04% (smoothed)