Similarly shaped airfoils to NACA65-112 a=0.6
New! Bulk download of polars in Excel format: NACA65-112%20a%3D0.6.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. NACA65-112 a=0.8
3. NACA65-112
4. NACA65-112 a=0.2
5. NACA65-112 a=0.0
6. NACA64A112
7. NACA63A112
8. NACA64-112 a=0.6
9. NACA64-112 a=0.5
10. NACA65A112
11. NACA64-112 a=0.8
12. NACA64(1)-112
13. R140 (original)
14. R140 12.04% (smoothed)
15. NACA64-112
16. NACA64-112 a=0.2
17. NACA64-112 a=0.0
18. NACA65-212
19. NACA65-212 a=0.0
20. NACA65A111
21. NACA65-113 a=0.6