Similarly shaped airfoils to NACA63-211 a=0.0
New! Bulk download of polars in Excel format: NACA63-211%20a%3D0.0.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. NACA64-211 a=0.0
3. NACA64-211 a=0.2
4. NACA63-211 a=0.5
5. NACA63-211
6. NACA64-211 a=0.5
7. NACA64-211
8. NACA63-211 a=0.6
9. NACA64-211 a=0.6
10. NACA63-111 a=0.5
11. NACA63-111 a=0.6
12. NACA64-111 a=0.5
13. NACA65-211 a=0.0
14. NACA63-211 a=0.8
15. NACA64-111 a=0.6
16. NACA65-211 a=0.2
17. NACA63-212 a=0.0
18. NACA63-210 a=0.0
19. NACA64-211 a=0.8
20. NACA63-212 a=0.2
21. NACA63-111 a=0.2