Similarly shaped airfoils to NACA66-517 a=0.6
New! Bulk download of polars in Excel format: NACA66-517%20a%3D0.6.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 a=0.8
3. NACA66A517
4. NACA66-518 a=0.6
5. NACA66-516 a=0.6
6. NACA66-617
7. NACA66-516 a=0.5
8. NACA66-518 a=0.5
9. NACA65A517
10. NACA66A617
11. NACA66-717
12. NACA66-518 a=0.8
13. NACA66-516 a=0.8
14. NACA66-617 a=0.5
15. NACA66A516
16. NACA66A518
17. NACA67-516 a=0.6
18. NACA66-417 a=0.6
19. NACA66-617 a=0.6
20. NACA66-617 a=0.8
21. NACA67-516 a=0.5