Similarly shaped airfoils to NACA66-620 a=0.2
New! Bulk download of polars in Excel format: NACA66-620%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. NACA66-620 a=0.0
3. NACA66-619 a=0.2
4. NACA66-520 a=0.5
5. NACA66-619 a=0.0
6. NACA66-719 a=0.0
7. NACA66-520 a=0.2
8. NACA66-720 a=0.2
9. NACA66-519 a=0.2
10. NACA66-520 a=0.6
11. NACA66-519 a=0.5
12. NACA66-620 a=0.5
13. NACA67-619 a=0.2
14. NACA66-719 a=0.2
15. NACA67-719 a=0.0
16. NACA66-520 a=0.0
17. NACA67-619 a=0.0
18. NACA67-620 a=0.2
19. NACA66-519 a=0.6
20. NACA66-420 a=0.5
21. NACA67-720 a=0.0