Similarly shaped airfoils to NACA65-611
New! Bulk download of polars in Excel format: NACA65-611.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. NACA64A511
3. NACA64-611
4. NACA63A511
5. NACA65A511
6. NACA64-511 a=0.8
7. NACA63-611
8. NACA65-612
9. NACA65-610
10. NACA63-511 a=0.8
11. NACA65A510
12. NACA66-611
13. NACA64-612
14. NACA65-511 a=0.6
15. NACA65-510 a=0.8
16. NACA64A510
17. NACA65-512 a=0.8
18. NACA66A511
19. HQ 3.0/11
20. NACA66-511 a=0.8
21. NACA66-610