Similarly shaped airfoils to GA 40-212
New! Bulk download of polars in Excel format: GA%2040-212.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
Dynamic plotter New!
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. GA 37A212
3. NACA65-312 a=0.5
4. NACA65-312 a=0.2
5. NACA65-312 a=0.6
6. GA 35A212
7. NACA65(1)-212 a=0.6
8. GA 37-212
9. NACA65-312 a=0.0
10. NACA65-312 a=0.8
11. NACA65-312
12. NACA64-312 a=0.5
13. NACA64-312 a=0.6
14. NACA64-312 a=0.2
15. NACA64A312
16. NACA63A312
17. NACA64-312 a=0.8
18. NACA65-412 a=0.0
19. NACA64-312
20. NACA64-312 a=0.0
21. NACA65-212 a=0.6