Similarly shaped airfoils to NACA63-511 a=0.6
New! Bulk download of polars in Excel format: NACA63-511%20a%3D0.6.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. NACA63-511 a=0.5
3. NACA64-511 a=0.5
4. GA 35-411
5. GA 37-411
6. K3311 (original)
7. K3311 (smoothed)
8. GA 35A411
9. NACA63-511 a=0.8
10. NACA64-511 a=0.8
11. NACA65-511 a=0.6
12. EPPLER E193gU-K24
13. EPPLER 193
14. NACA63-512 a=0.6
15. NACA63-510 a=0.6
16. GA 37A411
17. GA 40-411
18. MS3/11GPV
19. HQ 3.0/11
20. NACA65-511 a=0.5
21. NACA64-510 a=0.6