Similarly shaped airfoils to NACA67-710
New! Bulk download of polars in Excel format: NACA67-710.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. NACA67-610 a=0.8
3. NACA66-710
4. NACA66A610
5. NACA66-610 a=0.8
6. NACA66-711
7. NACA67-711
8. NACA67-709
9. NACA67-510 a=0.8
10. NACA66A611
11. NACA67A611
12. NACA67A609
13. NACA66-611 a=0.8
14. NACA67-611 a=0.8
15. NACA67-609 a=0.8
16. NACA67A510
17. NACA65A610
18. NACA65A611
19. NACA67-610 a=0.6
20. NACA66-510 a=0.8
21. NACA66-610