Similarly shaped airfoils to NACA65-114 a=0.5
New! Bulk download of polars in Excel format: NACA65-114%20a%3D0.5.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. NACA65-114 a=0.8
3. NACA65-114 a=0.2
4. NACA65(215)-114
5. NACA65-114
6. NACA65-114 a=0.0
7. NACA64A114
8. NACA63A114
9. NACA65-214 a=0.0
10. NACA64-114 a=0.5
11. NACA64-114 a=0.6
12. NACA64-114 a=0.8
13. NACA65A114
14. NACA64-114 a=0.2
15. NACA65-214
16. NACA64-114
17. NACA64-114 a=0.0
18. NACA65-115 a=0.5
19. NACA65-113 a=0.5
20. NACA65-115 a=0.6
21. NACA65-113 a=0.6