Similarly shaped airfoils to NACA63A611
New! Bulk download of polars in Excel format: NACA63A611.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. NACA64-611 a=0.8
3. NACA65-611 a=0.8
4. NACA64-711
5. NACA65-711
6. GOE 547
7. NACA63-611 a=0.8
8. NACA65A611
9. NACA63-711
10. NACA64-612 a=0.8
11. SG6042
12. NACA64-712
13. NACA63A612
14. NACA63A610
15. NACA63-612 a=0.8
16. NACA64A612
17. RAF 32 MOD
18. EPPLER 67
19. NACA64A610
20. NACA65-612 a=0.8
21. GOE 546