Similarly shaped airfoils to FX 77-W-121
New! Bulk download of polars in Excel format: fx77w121.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
Dynamic plotter New!
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. EPPLER 598
3. FX 05-H-126
4. NACA63-712 a=0.2
5. NACA63-712 a=0.0
6. MILEY M06-13-128
7. NACA63-711 a=0.0
8. EPPLER 334
9. EPPLER 639
10. NACA63-711 a=0.2
11. NACA64-712 a=0.0
12. NACA64-712 a=0.2
13. NACA64-711 a=0.0
14. EPPLER 593
15. NACA64-711 a=0.2
16. NACA63-612 a=0.2
17. NACA63-611 a=0.2
18. RAF 33
19. NACA45010.5
20. FAD21
21. MH 82 13.31%