Similarly shaped airfoils to FX 66-182
New! Bulk download of polars in Excel format: fx66182.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 66-17AII-182
3. AH 93-W-174
4. NACA63-618 a=0.6
5. NACA63(3)-618
6. NACA64(3)-618
7. NACA64-618 a=0.6
8. NACA63-618 a=0.5
9. NACA63-618 a=0.8
10. FX 66-S-171
11. EPPLER 655
12. NACA63-617 a=0.6
13. NACA63-718
14. GA 35-618
15. FX S 02-196
16. NACA64-617 a=0.6
17. NACA64-618 a=0.5
18. NACA63-617 a=0.5
19. NACA64-618 a=0.8
20. HQ 3.5/18
21. FX 66-S-196 V1