Similarly shaped airfoils to NACA66-509 a=0.5
New! Bulk download of polars in Excel format: NACA66-509%20a%3D0.5.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. NACA67-509 a=0.5
3. NACA65-509 a=0.5
4. NACA67-509 a=0.6
5. NACA65-509 a=0.6
6. NACA66-510 a=0.5
7. NACA65-510 a=0.5
8. NACA66-510 a=0.6
9. NACA65-510 a=0.6
10. NACA66-609 a=0.0
11. NACA66-609 a=0.2
12. NACA66-509 a=0.8
13. GA 40A410
14. GA 40-410
15. NACA66A509
16. NACA66-509 a=0.2
17. GA 37A410
18. NACA64-509 a=0.5
19. NACA65A509
20. NACA67-609 a=0.2
21. NACA66-609