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
Dynamic plotter New!
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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA63-609 a=0.0
3. NACA64-609 a=0.0
4. NACA63-509 a=0.2
5. NACA64-509 a=0.2
6. I.S.A. 960
7. NACA63-609 a=0.2
8. NACA63-610 a=0.0
9. NACA64-609 a=0.2
10. NACA64-610 a=0.0
11. NACA65-609 a=0.0
12. NACA65-509 a=0.2
13. NACA63-509 a=0.5
14. HL75-K-3
15. NACA63-510 a=0.2
16. NACA M17
17. SD6080 (9.2%)
18. EPPLER 176
19. NACA64-509 a=0.5
20. NACA63-610 a=0.2
21. NACA64-510 a=0.2