Similarly shaped airfoils to NACA0012-64 a=0.8 c(li)=0.2
New! Bulk download of polars in Excel format: NACA0012-64%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. NACA67-311 a=0.2
3. NACA67-311 a=0.5
4. NACA67-411 a=0.0
5. NACA67-311 a=0.6
6. NACA67-311 a=0.0
7. NACA67A311
8. NACA67-311 a=0.8
9. NACA67-411 a=0.2
10. NACA66-311 a=0.2
11. NACA66-311 a=0.5
12. NACA66-411 a=0.0
13. LOCKHEED C-141 BL761.11
14. NACA66-311 a=0.0
15. NACA66-311 a=0.6
16. LOCKHEED C-141 BL610.61
17. MH 25 9.98%
18. NACA66-312 a=0.2
19. NACA67-310 a=0.2
20. NACA66-312 a=0.5
21. NACA66-412 a=0.0