Similarly shaped airfoils to FX 66-S-196 V1
New! Bulk download of polars in Excel format: fx66196v.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. FX S 02-196
3. NACA64-719 a=0.8
4. NACA63-719 a=0.8
5. EPPLER 1098
6. GA 37-619
7. GA 35-619
8. NACA64-719 a=0.6
9. NACA64-720 a=0.8
10. FX 66-17AII-182
11. NACA64-718 a=0.8
12. NACA63-719 a=0.6
13. NACA63-720 a=0.8
14. HQ 3.5/18
15. NACA63-718 a=0.8
16. GA 37-618
17. NACA63-619 a=0.8
18. FX 66-182
19. FX 66-17AII-182
20. NACA63-619 a=0.6
21. NACA64-619 a=0.8