Similarly shaped airfoils to NACA66-509 a=0.6
New! Bulk download of polars in Excel format: NACA66-509%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. NACA67-509 a=0.6
3. NACA65-509 a=0.6
4. NACA67-509 a=0.5
5. NACA66-509 a=0.8
6. NACA66A509
7. NACA65-509 a=0.5
8. NACA65A509
9. NACA66-510 a=0.6
10. NACA66-609
11. NACA65-510 a=0.6
12. NACA67-509 a=0.8
13. NACA66-510 a=0.5
14. NACA65-510 a=0.5
15. NACA67A509
16. NACA65-509 a=0.8
17. GA 40A410
18. NACA64A509
19. GA 40-410
20. NACA66A609
21. NACA64-509 a=0.6