Similarly shaped airfoils to NACA65A112
New! Bulk download of polars in Excel format: NACA65A112.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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. NACA64A112
3. R140 12.04% (smoothed)
4. NACA66A112
5. NACA66-112 a=0.8
6. NACA66-112 a=0.6
7. NACA66-112
8. NACA65-112 a=0.8
9. NACA66-112 a=0.5
10. NACA65-112 a=0.6
11. NACA65-112
12. NACA65-112 a=0.5
13. NACA66-112 a=0.2
14. NACA66-112 a=0.0
15. NACA65-112 a=0.2
16. NACA65-112 a=0.0
17. NACA63A112
18. HAWKER TEMPEST 61% SEMISPAN
19. NACA65-113 a=0.8
20. NACA65-113 a=0.6
21. NACA65A113