Similarly shaped airfoils to NACA67-211 a=0.6
New! Bulk download of polars in Excel format: NACA67-211%20a%3D0.6.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. NACA67-211 a=0.8
3. NACA67A211
4. NACA67-211 a=0.2
5. NACA67-211
6. NACA67-211 a=0.0
7. NACA67-311 a=0.0
8. NACA66-211 a=0.6
9. NACA66-211 a=0.5
10. MH 26 10.99%
11. NACA66-211 a=0.8
12. NACA66A211
13. NACA67-311 a=0.2
14. NACA67-212 a=0.6
15. NACA67-210 a=0.6
16. NACA66-212 a=0.6
17. NACA67-210 a=0.5
18. NACA66-211 a=0.2
19. NACA 66,2-(1.8)12 A=.6 P-51 TIP
20. NACA67-212 a=0.5
21. NACA66-212 a=0.5