Similarly shaped airfoils to FX S 02-196
New! Bulk download of polars in Excel format: fxs02196.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 66-S-196
3. EPPLER 1098
4. NACA63-719 a=0.8
5. NACA64-719 a=0.8
6. HQ 3.5/18
7. NACA63-619 a=0.8
8. FX 66-17AII-182
9. NACA63-719
10. NACA63-619 a=0.6
11. NACA64-619 a=0.8
12. GA 35-619
13. NACA63-720 a=0.8
14. FX 66-182
15. NACA64-720 a=0.8
16. FX 66-17AII-182
17. NACA63(3)-618
18. GA 37-619
19. NACA64-719
20. NACA64(3)-618
21. NACA64-619 a=0.6