Similarly shaped airfoils to EPPLER 220
New! Bulk download of polars in Excel format: e220.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. NACA64-412 a=0.2
3. NACA63-412 a=0.2
4. NACA64-512 a=0.0
5. NACA63-512 a=0.0
6. EPPLER 374
7. NACA64-412 a=0.0
8. NACA63-412 a=0.0
9. NACA64-411 a=0.2
10. NACA65-412 a=0.2
11. GA 35A312
12. NACA63-411 a=0.2
13. GA 37-312
14. EPPLER 207
15. NACA64-412 a=0.5
16. NACA65-411 a=0.2
17. NACA63-412 a=0.5
18. GA 30-311
19. GA 35A311
20. GA 35-312
21. GA 37A312