Similarly shaped airfoils to NACA67-712
New! Bulk download of polars in Excel format: NACA67-712.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. NACA67-612 a=0.8
3. NACA66-712
4. NACA66A612
5. NACA67-713
6. NACA67-711
7. NACA67-512 a=0.8
8. NACA67-612
9. NACA66-713
10. NACA66-612 a=0.8
11. NACA67A613
12. NACA67A611
13. NACA67-613 a=0.8
14. NACA66A613
15. NACA67A512
16. NACA67-611 a=0.8
17. NACA66-613 a=0.8
18. FX 74-130 WP1
19. NACA67-612 a=0.6
20. NACA67-512 a=0.6
21. NACA66-512 a=0.8