Similarly shaped airfoils to NACA66-718 a=0.5
New! Bulk download of polars in Excel format: NACA66-718%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. NACA66-719 a=0.5
3. NACA66-717 a=0.5
4. NACA66-719 a=0.6
5. NACA66-717 a=0.6
6. NACA66-618 a=0.5
7. NACA66-618 a=0.6
8. NACA67-717 a=0.5
9. NACA67-718 a=0.5
10. NACA67-717 a=0.6
11. NACA66-617 a=0.5
12. NACA66-617 a=0.6
13. NACA65-719 a=0.5
14. NACA67-718 a=0.6
15. NACA66-718 a=0.8
16. NACA66A718
17. GA 40A619
18. NACA65-718 a=0.5
19. GA 40-619
20. NACA66-619 a=0.6
21. NACA66-619 a=0.5