Similarly shaped airfoils to NACA66-210 a=0.8
New! Bulk download of polars in Excel format: NACA66-210%20a%3D0.8.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
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2. NACA66-210 a=0.6
3. NACA66-210 a=0.5
4. NACA66-210
5. NACA65A210
6. NACA66-310
7. NACA0010-34 a=0.8 c(li)=0.2
8. NACA67-210 a=0.8
9. NACA67A210
10. NACA66-210 a=0.2
11. NACA67-210 a=0.6
12. NACA66-210 a=0.0
13. NACA65-210 a=0.8
14. NACA67-210 a=0.5
15. EPPLER 904
16. NACA67-210
17. NACA65-210 a=0.6
18. NACA67-209 a=0.8
19. NACA67A209
20. NACA64A210
21. NACA65A211