Similarly shaped airfoils to FX 78-K-161
New! Bulk download of polars in Excel format: fx78k161.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. NACA65-516 a=0.0
3. NACA65-517 a=0.0
4. NACA65-416 a=0.2
5. NACA65-516 a=0.2
6. NACA65-517 a=0.2
7. NACA65-417 a=0.2
8. FX 75-VG-166/22
9. NACA65-416 a=0.5
10. EPPLER 642
11. NACA65-417 a=0.5
12. NACA65-416 a=0.0
13. GA 40-316
14. GA 40A316
15. NACA66-516 a=0.0
16. GA 40-317
17. NACA64-517 a=0.0
18. NACA65-617 a=0.0
19. NACA65-616 a=0.0
20. GA 40A317
21. NACA64-517 a=0.2