Similarly shaped airfoils to FX 66-17A-175
New! Bulk download of polars in Excel format: fx66a175.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. FX 66-S-161
3. GOE 425
4. GA 35-616
5. GA 35-617
6. NACA63-716 a=0.6
7. GA 37-616
8. NACA63-716 a=0.8
9. NACA63-717 a=0.6
10. NACA63-716 a=0.5
11. NACA63-717 a=0.8
12. GA 37-617
13. NACA63-717 a=0.5
14. FX 66-182
15. FX 66-17AII-182
16. AH 93-W-174
17. NACA63-616 a=0.6
18. EPPLER 793
19. GOE 413
20. EPPLER 856
21. FX 63-158