Similarly shaped airfoils to EPPLER 393
New! Bulk download of polars in Excel format: e393.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (3) | 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. NACA63-611 a=0.8
3. NACA63-711
4. NACA63-612 a=0.8
5. NACA64-611 a=0.8
6. FX 83-W-108
7. NACA63-712
8. NACA64-711
9. GOE 547
10. NACA64-612 a=0.8
11. NACA63-611 a=0.6
12. JWL041 11/3.5
13. GOE 723
14. NACA63A611
15. RAF 32 MOD
16. HQ 3.5/12
17. NACA63-612 a=0.6
18. NACA64-712
19. NACA63-712 a=0.8
20. NACA64-611 a=0.6
21. NACA63-711 a=0.8