Similarly shaped airfoils to NACA65A511
New! Bulk download of polars in Excel format: NACA65A511.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. NACA66A511
3. NACA66-511 a=0.8
4. NACA65-511 a=0.8
5. NACA66-611
6. NACA65-611
7. NACA63A511
8. NACA65-512 a=0.8
9. NACA64A512
10. NACA65-612
11. NACA65A512
12. NACA65A510
13. NACA66A510
14. NACA66-510 a=0.8
15. NACA66-511 a=0.6
16. NACA66-610
17. NACA65-511 a=0.6
18. NACA64-511 a=0.8
19. GOE 673
20. NACA63A512
21. NACA64-611