Similarly shaped airfoils to NACA67-510 a=0.8
New! Bulk download of polars in Excel format: NACA67-510%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. NACA66-510 a=0.8
3. NACA66A510
4. NACA67-510 a=0.6
5. NACA66-610
6. NACA66-511 a=0.8
7. NACA66A511
8. NACA67-511 a=0.8
9. NACA67-509 a=0.8
10. NACA67A509
11. NACA67A511
12. NACA66-611
13. NACA67-710
14. NACA67-611
15. NACA66-510 a=0.6
16. NACA65A510
17. NACA67A610
18. NACA67-510 a=0.5
19. NACA65A511
20. NACA66-511 a=0.6
21. NACA67-511 a=0.6