Similarly shaped airfoils to NACA66A516
New! Bulk download of polars in Excel format: NACA66A516.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. NACA66-616
3. NACA65A516
4. NACA66-516 a=0.6
5. NACA66A517
6. NACA66-517 a=0.8
7. NACA66A515
8. NACA66-515 a=0.8
9. NACA66-617
10. NACA66-615
11. NACA66-516
12. NACA65A517
13. NACA66-716
14. NACA66-416 a=0.8
15. NACA66-516 a=0.5
16. NACA66-416 a=0.6
17. NACA66A416
18. NACA67A515
19. NACA67-515 a=0.8
20. NACA66A616
21. NACA67-615