Similarly shaped airfoils to NACA66-217 a=0.0


Direct link: NACA66-217 a=0.0
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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1. NACA66-217 a=0.2
2. NACA66-117 a=0.5
3. NACA66-117 a=0.6
4. NACA66-217 a=0.5
5. NACA66-217
6. NACA66-117 a=0.2
7. NACA66-117 a=0.8
8. NACA66-217 a=0.6
9. NACA66A117
10. NACA66-117 a=0.0
11. NACA66A217
12. NACA66-217 a=0.8
13. NACA66-317 a=0.0
14. NACA66-218 a=0.0
15. NACA66-216 a=0.0
16. NACA66-218 a=0.2
17. NACA66-117
18. NACA66-216 a=0.2
19. NACA66-116 a=0.5
20. NACA66-218 a=0.5
21. NACA66-116 a=0.6