Similarly shaped airfoils to NACA67-509 a=0.2
New! Bulk download of polars in Excel format: NACA67-509%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
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. NACA67-609 a=0.0
3. NACA66-509 a=0.2
4. NACA66-509 a=0.0
5. NACA66-510 a=0.2
6. NACA66-609 a=0.0
7. NACA67-409 a=0.5
8. NACA67-510 a=0.2
9. NACA66-510 a=0.0
10. NACA66-610 a=0.0
11. NACA67-610 a=0.0
12. NACA67-510 a=0.0
13. NACA67-509 a=0.5
14. NACA66-409 a=0.5
15. NACA67-409 a=0.2
16. NACA67-609 a=0.2
17. NACA67-409 a=0.6
18. NACA66-409 a=0.2
19. NACA66-410 a=0.5
20. NACA66-509 a=0.5
21. NACA65-510 a=0.2