Similarly shaped airfoils to NACA67-511 a=0.8
New! Bulk download of polars in Excel format: NACA67-511%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. NACA67-611
3. NACA67-511 a=0.6
4. NACA66-511 a=0.8
5. NACA66A511
6. NACA66-611
7. NACA67-512 a=0.8
8. NACA67-510 a=0.8
9. NACA67A510
10. NACA66-512 a=0.8
11. NACA66A512
12. NACA67A512
13. NACA67-711
14. NACA67-612
15. NACA66-612
16. NACA67A611
17. NACA67-511 a=0.5
18. NACA66-511 a=0.6
19. NACA65A511
20. NACA65A512
21. NACA67-411 a=0.8