Similarly shaped airfoils to NACA66-718 a=0.6
New! Bulk download of polars in Excel format: NACA66-718%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
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. NACA66-719 a=0.6
3. NACA66-717 a=0.6
4. NACA66-718 a=0.8
5. NACA66-717 a=0.5
6. NACA66-719 a=0.5
7. NACA66A718
8. NACA66-618 a=0.6
9. NACA67-717 a=0.6
10. NACA66-719 a=0.8
11. NACA66-717 a=0.8
12. NACA67-718 a=0.6
13. NACA65A718
14. NACA67-717 a=0.5
15. NACA66A717
16. NACA66-618 a=0.5
17. NACA66A719
18. NACA66-617 a=0.6
19. NACA65-719 a=0.6
20. NACA67-718 a=0.5
21. NACA65-718 a=0.6