Similarly shaped airfoils to FX 05-H-126
New! Bulk download of polars in Excel format: fx05h126.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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. NACA63-712 a=0.2
3. NACA64-712 a=0.0
4. FX 77-W-121
5. NACA63-713 a=0.0
6. NACA63-713 a=0.2
7. NACA64-712 a=0.2
8. NACA63-612 a=0.2
9. MILEY M06-13-128
10. NACA64-713 a=0.0
11. NACA64-713 a=0.2
12. NACA64-612 a=0.2
13. RAF 33
14. NACA63-613 a=0.2
15. NACA63-711 a=0.0
16. NACA64-613 a=0.2
17. EPPLER 638
18. AH 80-140
19. NACA64-711 a=0.0
20. NACA65-712 a=0.0
21. NACA63-711 a=0.2