Similarly shaped airfoils to NACA66A417
New! Bulk download of polars in Excel format: NACA66A417.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. NACA66-517
3. NACA66-417 a=0.6
4. NACA66-417
5. NACA65A417
6. NACA66-417 a=0.5
7. NACA66-418 a=0.8
8. NACA66A418
9. NACA66A416
10. NACA66-416 a=0.8
11. NACA66-518
12. NACA66-516
13. EPPLER 664
14. NACA66(3)-418
15. NACA66(215)-416
16. NACA66-317 a=0.8
17. NACA66-317 a=0.6
18. NACA65A418
19. NACA66-418 a=0.6
20. NACA66A317
21. NACA66-416 a=0.6