Similarly shaped airfoils to NACA65A113
New! Bulk download of polars in Excel format: NACA65A113.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. NACA66A113
3. NACA66-113 a=0.8
4. NACA66-113 a=0.6
5. NACA66-113
6. NACA66-113 a=0.5
7. NACA65-113 a=0.8
8. NACA65-113 a=0.6
9. NACA65-113
10. NACA65-113 a=0.5
11. NACA66-113 a=0.2
12. NACA66-113 a=0.0
13. NACA65-113 a=0.2
14. NACA65-113 a=0.0
15. NACA63A113
16. NACA65A114
17. NACA65A112
18. NACA65-114 a=0.8
19. NACA65-114 a=0.6
20. NACA65(215)-114
21. NACA64A114