Similarly shaped airfoils to NACA66-110 a=0.5
New! Bulk download of polars in Excel format: NACA66-110%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. NACA66-110 a=0.8
3. NACA66A110
4. NACA66-110 a=0.2
5. NACA66-110 a=0.0
6. NACA66-110
7. NACA65A110
8. NACA67-110 a=0.5
9. NACA67-110 a=0.6
10. NACA67-110 a=0.8
11. NACA67A110
12. NACA67-110 a=0.2
13. NACA67-110
14. NACA67-110 a=0.0
15. NACA66-210
16. NACA66-210 a=0.0
17. NACA65-110 a=0.5
18. NACA65-110 a=0.6
19. NACA65-110 a=0.8
20. NACA65-110 a=0.2
21. NACA65-110 a=0.0