Similarly shaped airfoils to EPPLER 178


New! Bulk download of polars in Excel format: e178.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.

1. NACA63-409 a=0.5
2. EPPLER 180
3. EPPLER 176
4. NACA64-409 a=0.5
5. NACA63-409 a=0.2
6. NACA63-509 a=0.0
7. MH 32 8.7%
8. NACA63-409 a=0.6
9. MID 327 9%
10. NACA64-409 a=0.2
11. AG3516
12. NACA64-509 a=0.0
13. GOE 622
14. MID 29
15. HN-418
16. NACA64-409 a=0.6
17. NACA63-509 a=0.2
18. S3021-095-84
19. GOE 566
20. NM23
21. SD7080 (9.2%)