Similarly shaped airfoils to NACA66-510 a=0.5
New! Bulk download of polars in Excel format: NACA66-510%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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA67-510 a=0.5
3. NACA67-510 a=0.6
4. NACA65-510 a=0.5
5. NACA67-509 a=0.5
6. NACA65-510 a=0.6
7. NACA66-511 a=0.5
8. NACA66-509 a=0.5
9. NACA65-511 a=0.5
10. NACA67-509 a=0.6
11. NACA66-511 a=0.6
12. NACA66-509 a=0.6
13. NACA66-610 a=0.2
14. NACA66-610 a=0.0
15. GA 40A410
16. NACA65-511 a=0.6
17. GA 40-410
18. NACA66-510 a=0.8
19. GA 37A410
20. NACA66A510
21. GA 40A411