Similarly shaped airfoils to NACA65-612 a=0.6
New! Bulk download of polars in Excel format: NACA65-612%20a%3D0.6.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. NACA64-612 a=0.6
3. GA 40-612
4. GA 40A612
5. NACA64-612 a=0.5
6. GA 37A612
7. NACA65-613 a=0.6
8. NACA65-611 a=0.6
9. NACA63-612 a=0.6
10. NACA65-612 a=0.8
11. GA 35A612
12. NACA64-613 a=0.6
13. NACA66-612 a=0.6
14. NACA65-611 a=0.5
15. NACA65-613 a=0.5
16. GA 37-612
17. NACA66-611 a=0.6
18. NACA63-612 a=0.5
19. NACA64A612
20. NACA64-613 a=0.5
21. NACA66-612 a=0.5