Similarly shaped airfoils to NACA66-211 a=0.5
New! Bulk download of polars in Excel format: NACA66-211%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. NACA66-211 a=0.8
3. NACA66A211
4. NACA66-211 a=0.2
5. NACA66-211 a=0.0
6. NACA66-211
7. NACA65A211
8. NACA66-311 a=0.0
9. NACA66-311
10. P-51D TIP (BL215)
11. NACA67-211 a=0.5
12. NACA67-211 a=0.6
13. NACA67-211 a=0.8
14. NACA67A211
15. NACA65-211 a=0.5
16. NACA66-311 a=0.2
17. NACA65-211 a=0.6
18. NACA66-212 a=0.5
19. NACA66-210 a=0.5
20. NACA67-211 a=0.2
21. NACA67-210 a=0.5