Similarly shaped airfoils to FX 78-K-140/20
New! Bulk download of polars in Excel format: fx78k140.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
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2. NACA65-614 a=0.5
3. NACA66-614 a=0.5
4. AH 81-K-144/17
5. NACA65-615 a=0.5
6. FX 78-K-150/20
7. NACA65-614 a=0.6
8. GA 40A614
9. GA 40-614
10. NACA66-613 a=0.5
11. NACA65-714 a=0.2
12. NACA66-614 a=0.6
13. NACA65-714 a=0.5
14. GA 40A615
15. NACA66-714 a=0.2
16. GA 40-615
17. AH 80-129
18. NACA65-615 a=0.6
19. GA 37A614
20. NACA65-715 a=0.5
21. NACA66-714 a=0.5