Similarly shaped airfoils to FX 66-S-161
New! Bulk download of polars in Excel format: fx66s161.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 66-17A-175
3. NACA63-615 a=0.6
4. NACA63-616 a=0.6
5. MID 415
6. GA 35-616
7. FX S 02/1-158
8. GA 35-615
9. NACA63-615 a=0.5
10. NACA63-616 a=0.5
11. NACA63-615 a=0.8
12. NACA63-616 a=0.8
13. NACA63-715
14. NACA64-615 a=0.6
15. NACA63-716
16. AH 93-W-145
17. FX 84-W-150
18. NACA64-616 a=0.6
19. MS3,3-15GP
20. NACA63(2)-615
21. GOE 425