Similarly shaped airfoils to FX 73-K-170/22
New! Bulk download of polars in Excel format: fx73k170.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. EPPLER 587
3. EPPLER 435
4. NACA65-717 a=0.8
5. EPPLER 654
6. NACA64-717 a=0.8
7. NACA65-716 a=0.8
8. EPPLER 656
9. NACA64A717
10. EPPLER 657
11. NACA63A717
12. NACA65-718 a=0.8
13. Dees Okay230
14. NACA65-717 a=0.6
15. NACA63-717 a=0.8
16. NACA64A716
17. NACA64-718 a=0.8
18. NACA63A716
19. NACA64-716 a=0.8
20. NACA65A716
21. NACA64-717 a=0.6