Similarly shaped airfoils to EPPLER 542
New! Bulk download of polars in Excel format: e542.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
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. NACA66-317 a=0.2
3. NACA66-417 a=0.0
4. EPPLER 544
5. NACA66-317 a=0.0
6. NACA66-316 a=0.2
7. NACA66-417 a=0.2
8. GA 40A217
9. NACA66-416 a=0.0
10. NACA66-317 a=0.5
11. GA 40-217
12. NACA65-317 a=0.2
13. NACA65-417 a=0.0
14. NACA66-316 a=0.0
15. GA 40A218
16. GA 37A217
17. GA 40-218
18. NACA66-317 a=0.6
19. EPPLER 546
20. NACA65-418 a=0.0
21. NACA66-316 a=0.5