Similarly shaped airfoils to NACA65A612
New! Bulk download of polars in Excel format: NACA65A612.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
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2. NACA66A612
3. NACA66-612 a=0.8
4. NACA65-612 a=0.8
5. NACA66-712
6. NACA65-712
7. NACA63A612
8. NACA65-613 a=0.8
9. NACA65A613
10. NACA65A611
11. NACA64A613
12. NACA66A611
13. NACA66-611 a=0.8
14. NACA65-713
15. NACA66-711
16. NACA63A613
17. CLARK V
18. SG6051
19. NACA66-612 a=0.6
20. NACA65-612 a=0.6
21. NACA64-612 a=0.8