Similarly shaped airfoils to FX 66-S-196
New! Bulk download of polars in Excel format: fx66s196.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. FX S 02-196
3. EPPLER 1098
4. NACA64-719 a=0.8
5. NACA64-619 a=0.8
6. NACA64-720 a=0.8
7. NACA64-619 a=0.6
8. NACA64-719
9. NACA63-619 a=0.8
10. EPPLER 604
11. NACA63-719 a=0.8
12. GA 37-619
13. NACA65-619 a=0.8
14. FX 66-17AII-182
15. NACA63-619 a=0.6
16. NACA64-620 a=0.8
17. NACA63-719
18. HQ 3.5/18
19. NACA65-619 a=0.6
20. NACA65-719
21. NACA63-720 a=0.8