Similarly shaped airfoils to NACA66-513 a=0.0
New! Bulk download of polars in Excel format: NACA66-513%20a%3D0.0.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. NACA66-413 a=0.2
3. NACA66-413 a=0.5
4. NACA66-514 a=0.0
5. NACA66-512 a=0.0
6. NACA67-513 a=0.0
7. NACA67-512 a=0.0
8. EPPLER 231
9. NACA66-514 a=0.2
10. NACA66-413 a=0.0
11. NACA66-613 a=0.0
12. NACA67-513 a=0.2
13. NACA66-512 a=0.2
14. NACA65-513 a=0.0
15. NACA66-412 a=0.2
16. NACA67-512 a=0.2
17. NACA66-413 a=0.6
18. AH 88-K-136/16
19. NACA65-514 a=0.0
20. NACA66-414 a=0.2
21. NACA67-412 a=0.2