Similarly shaped airfoils to NACA66-718 a=0.8
New! Bulk download of polars in Excel format: NACA66-718%20a%3D0.8.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. NACA65A718
3. NACA66-719 a=0.8
4. NACA66-717 a=0.8
5. NACA66A717
6. NACA66A719
7. NACA66-718 a=0.6
8. NACA65A719
9. NACA66-618 a=0.8
10. NACA67-717 a=0.8
11. NACA67A717
12. NACA66A618
13. NACA66-618 a=0.6
14. NACA66-719 a=0.6
15. NACA67-718 a=0.8
16. NACA66-717 a=0.6
17. NACA65A717
18. NACA67A718
19. NACA66-617 a=0.8
20. NACA65-719 a=0.8
21. NACA65A618