Similarly shaped airfoils to NACA65-113
New! Bulk download of polars in Excel format: NACA65-113.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. NACA65-113 a=0.6
3. NACA65-113 a=0.5
4. NACA65-113 a=0.2
5. NACA65-113 a=0.0
6. NACA64A113
7. NACA63A113
8. NACA64-113
9. NACA65A113
10. NACA64-113 a=0.8
11. NACA64-113 a=0.6
12. NACA64-113 a=0.5
13. NACA64-113 a=0.2
14. NACA64-113 a=0.0
15. NACA65-114
16. NACA65-112
17. NACA65(215)-114
18. GA 40-013
19. GA 40A013
20. NACA65-114 a=0.8
21. NACA65A112