Similarly shaped airfoils to NACA65-510 a=0.2
New! Bulk download of polars in Excel format: NACA65-510%20a%3D0.2.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. NACA64-510 a=0.2
3. NACA65-610 a=0.0
4. NACA64-510 a=0.0
5. NACA63-510 a=0.2
6. NACA64-610 a=0.0
7. NACA66-510 a=0.2
8. NACA65-511 a=0.2
9. NACA65-509 a=0.2
10. NACA64-511 a=0.2
11. NACA63-510 a=0.0
12. NACA63-610 a=0.0
13. NACA65-410 a=0.5
14. NACA66-509 a=0.2
15. NACA66-510 a=0.0
16. GA 40-410
17. GA 40A410
18. NACA65-509 a=0.0
19. GA 37A410
20. NACA66-509 a=0.0
21. NACA64-611 a=0.0