Similarly shaped airfoils to NACA66-410 a=0.5
New! Bulk download of polars in Excel format: NACA66-410%20a%3D0.5.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. NACA67-410 a=0.5
3. NACA67-410 a=0.6
4. NACA65-410 a=0.5
5. DP2.47/9.48_DS
6. NACA66-510 a=0.0
7. NACA66-410 a=0.8
8. NACA66A410
9. NACA65-410 a=0.6
10. NACA66-410 a=0.2
11. NACA67-409 a=0.5
12. NACA66-411 a=0.5
13. NACA66-409 a=0.5
14. NACA66-510 a=0.2
15. NACA67-409 a=0.6
16. NACA66-510
17. NACA66-411 a=0.6
18. NACA65-411 a=0.5
19. NACA66-409 a=0.6
20. NACA65A410
21. NACA65-411 a=0.6