Similarly shaped airfoils to FX 83-W-108
New! Bulk download of polars in Excel format: fx83w108.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. RAF 32 MOD
3. EPPLER 66
4. EPPLER 214
5. NACA63-611 a=0.8
6. EPPLER 393
7. NACA64-611 a=0.8
8. NACA63A611
9. NACA63A711
10. NACA63-711
11. NACA64-711
12. NACA64A611
13. MH 116 9.84%
14. NACA63-711 a=0.8
15. S4022
16. EPPLER 67
17. NACA64A711
18. NACA63A610
19. NACA63-612 a=0.8
20. NACA64-711 a=0.8
21. NACA65-611 a=0.8