Similarly shaped airfoils to EPPLER 904
New! Bulk download of polars in Excel format: e904.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. NACA67A209
3. NACA67-209 a=0.6
4. NACA67-209 a=0.5
5. NACA67-209
6. NACA66-209 a=0.8
7. NACA66A209
8. NACA66-209 a=0.6
9. MH 24 9.01%
10. NACA66-209 a=0.5
11. NACA67-209 a=0.2
12. NACA66-209
13. NACA66-309
14. NACA65A209
15. NACA66-210 a=0.8
16. NACA66A210
17. NACA66-210 a=0.6
18. NACA67-209 a=0.0
19. NACA0010-34 a=0.8 c(li)=0.2
20. NACA65A210
21. NACA66-209 a=0.2