Similarly shaped airfoils to NACA64A511
New! Bulk download of polars in Excel format: NACA64A511.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. NACA65-511 a=0.8
3. NACA65-611
4. NACA65A511
5. NACA64-511 a=0.8
6. NACA64-611
7. NACA63-511 a=0.8
8. GOE 673
9. NACA63-611
10. NACA64-512 a=0.8
11. HQ 3.0/11
12. NACA65A510
13. NACA64A512
14. NACA64A510
15. NACA65-511 a=0.6
16. NACA63A510
17. NACA64-612
18. NACA65-512 a=0.8
19. GA 37A411
20. NACA63A512
21. NACA65-612