Similarly shaped airfoils to FX 66-17AII-182
New! Bulk download of polars in Excel format: fx6617ai.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 66-182
3. NACA63-718
4. GA 35-418
5. NACA63(3)-618
6. NACA63-618 a=0.6
7. AH 93-W-174
8. NACA63-618 a=0.8
9. FX S 02-196
10. NACA64(3)-618
11. NACA64-718
12. GA 37-418
13. NACA63-618 a=0.5
14. NACA64-618 a=0.6
15. NACA64-618 a=0.8
16. NACA63-719
17. FX 66-S-196 V1
18. NACA64-618 a=0.5
19. GA 35-419
20. FX 66-S-196
21. NACA63-619 a=0.6