Similarly shaped airfoils to EPPLER 66
New! Bulk download of polars in Excel format: e66.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. RAF 32 MOD
3. MH 116 9.84%
4. FX 83-W-108
5. NACA63A710
6. SG6041_PSO
7. PSU 94-097 (AIAA 2001-2478)
8. NACA64A710
9. S4022
10. GOE 547
11. NACA5510
12. NACA63-711 a=0.8
13. NACA63A711
14. NACA63-710 a=0.8
15. S4062-095-87
16. NACA64-711 a=0.8
17. NACA63A610
18. NACA64-710 a=0.8
19. NACA63-610 a=0.8
20. AF140k
21. NACA64-610 a=0.8