Similarly shaped airfoils to NACA64-612 a=0.8
New! Bulk download of polars in Excel format: NACA64-612%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. NACA64-712
3. NACA63-712
4. NACA63A612
5. NACA65-612 a=0.8
6. NACA64A612
7. NACA65-712
8. NACA63A611
9. EPPLER 67
10. HQ 3.5/12
11. NACA64-613 a=0.8
12. NACA64-611 a=0.8
13. NACA64A611
14. NACA64-612 a=0.6
15. NACA63-611 a=0.8
16. NACA63-613 a=0.8
17. NACA65-611 a=0.8
18. NACA63-612 a=0.6
19. NACA64-711
20. NACA64-713
21. EPPLER 393