Similarly shaped airfoils to FX 75-141
New! Bulk download of polars in Excel format: fx75141.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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. NACA63-714
3. NACA64-715
4. NACA63-715
5. NACA63(2)-615
6. NACA64-614 a=0.8
7. NACA63-614 a=0.8
8. NACA64-615 a=0.8
9. HQ 3.5/14
10. NACA65-714
11. NACA63-615 a=0.8
12. NACA63A614
13. HQ 3.0/14
14. EPPLER 68
15. NACA64-614
16. NACA63-614
17. NACA64-514 a=0.8
18. NACA63-514 a=0.8
19. NACA64A614
20. NACA65-614 a=0.8
21. EM J18 1 3015