Similarly shaped airfoils to NACA66-410
New! Bulk download of polars in Excel format: NACA66-410.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. NACA66A310
3. NACA66-310 a=0.6
4. NACA65A310
5. NACA66-310 a=0.5
6. NACA66A410
7. NACA65-410
8. NACA67-310 a=0.8
9. NACA67A310
10. NACA66-410 a=0.8
11. NACA65A410
12. NACA66-411
13. NACA65-310 a=0.8
14. NACA66-409
15. NACA67-310 a=0.6
16. NACA65-411
17. NACA67-309 a=0.8
18. NACA66-309 a=0.8
19. NACA67A309
20. NACA66-310
21. NACA66-510