Similarly shaped airfoils to FX 78-K-140 A/20
New! Bulk download of polars in Excel format: fx78k140a20.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. AH 81-K-144/17
3. NACA65-614 a=0.5
4. GA 40A614
5. GA 40-614
6. FX 78-K-150/20
7. NACA66-614 a=0.5
8. GA 40A615
9. GA 40-615
10. NACA65-614 a=0.6
11. GA 37A614
12. NACA65-615 a=0.5
13. EPPLER 434
14. NACA66-614 a=0.6
15. NACA66-613 a=0.5
16. NACA65-714 a=0.5
17. NACA65-615 a=0.6
18. NACA66-714 a=0.5
19. AH 80-129
20. NACA65-715 a=0.5
21. GA 37A615