Similarly shaped airfoils to FX 78-K-150/20
New! Bulk download of polars in Excel format: fx78k150.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. NACA65-615 a=0.5
3. FX 78-K-140 A/20
4. NACA65-615 a=0.6
5. NACA66-615 a=0.5
6. GA 40A615
7. GA 40-615
8. NACA66-615 a=0.6
9. FX 78-K-140/20
10. NACA65-616 a=0.5
11. NACA66-614 a=0.5
12. NACA65-616 a=0.6
13. GA 40-616
14. NACA66-614 a=0.6
15. GA 40A616
16. GA 37A615
17. AH 83-159
18. NACA65-715 a=0.5
19. AH 94-156
20. NACA65-614 a=0.5
21. NACA66-715 a=0.5