Similarly shaped airfoils to EPPLER 231
New! Bulk download of polars in Excel format: e231.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. GA 40A313
3. NACA66-413 a=0.5
4. GA 40-313
5. NACA66-413 a=0.2
6. NACA66-412 a=0.2
7. NACA65-413 a=0.5
8. Jedeslsky EJ1
9. NACA65-413 a=0.2
10. GA 35A313
11. NACA66-412 a=0.5
12. NACA66-513 a=0.0
13. NACA65-513 a=0.0
14. NACA66-413 a=0.6
15. NACA66-512 a=0.0
16. NACA65-413 a=0.6
17. NACA66-412 a=0.6
18. NACA66-412 a=0.0
19. NACA65A413
20. NACA66-413 a=0.0
21. Bambino 6