Similarly shaped airfoils to FX 67-K-170/17
New! Bulk download of polars in Excel format: fx67k170.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (16) | 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. FX 73-170 A
3. NACA65-717 a=0.6
4. NACA65-717 a=0.5
5. GA 40-617
6. GA 40A617
7. EPPLER 657
8. EPPLER 583
9. EPPLER 654
10. GA 40-618
11. NACA65-718 a=0.6
12. GA 37A617
13. GA 40A618
14. NACA65-716 a=0.6
15. NACA65-716 a=0.5
16. NACA65-718 a=0.5
17. NACA66-716 a=0.6
18. NACA66-716 a=0.5
19. EPPLER 584
20. NACA66-717 a=0.6
21. AH 95-160