Similarly shaped airfoils to EPPLER 266
New! Bulk download of polars in Excel format: e266.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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
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. NACA65-518 a=0.2
3. GA 40A318
4. GA 40A317
5. GA 40-318
6. GA 40-317
7. EPPLER 664
8. GA 37A317
9. NACA65-618 a=0.0
10. NACA65-417 a=0.5
11. NACA65-418 a=0.5
12. NACA65-517 a=0.0
13. RONCZ 1080 VOYAGER INNER AFT WING
14. NACA65-617 a=0.0
15. FX 75-VG-166/22
16. NACA65-518 a=0.0
17. GA 37A318
18. RONCZ 1082 VOYAGER ROOT OUTER AFT WING
19. NACA65-518 a=0.5
20. NACA65-418 a=0.6
21. GA 35A317