Similarly shaped airfoils to Eiffel 428 (Bleriot)
New! Bulk download of polars in Excel format: eiffel428.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. NACA64-609 a=0.0
3. NACA63-509 a=0.2
4. NACA64-509 a=0.2
5. I.S.A. 960
6. NACA63-609 a=0.2
7. NACA63-610 a=0.0
8. NACA64-609 a=0.2
9. NACA64-610 a=0.0
10. NACA65-609 a=0.0
11. NACA65-509 a=0.2
12. NACA63-509 a=0.5
13. HL75-K-3
14. NACA63-510 a=0.2
15. NACA M17
16. SD6080 (9.2%)
17. EPPLER 176
18. NACA64-509 a=0.5
19. NACA63-610 a=0.2
20. NACA64-510 a=0.2
21. EPPLER 387