Similarly shaped airfoils to EPPLER 554
New! Bulk download of polars in Excel format: e554.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. NACA63-618
3. NACA63-617
4. NACA63(420)-517
5. NACA63-518 a=0.8
6. NACA63-517 a=0.8
7. NACA63(3)-418
8. NACA63-517
9. NACA63-518
10. MH 102 16.99%
11. NACA64-617
12. NACA63-718
13. NACA64-618
14. Joukowsky 18.00% thick 3.00% camber
15. NACA63(3)-618
16. NACA63-417 a=0.8
17. NACA63-717
18. NACA63-418 a=0.8
19. NLF(1)-0416
20. NACA64-517 a=0.8
21. GA 35-317