Similarly shaped airfoils to NACA64-412 a=0.5
New! Bulk download of polars in Excel format: NACA64-412%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. NACA64-412 a=0.6
3. GA 37-312
4. NACA63-412 a=0.6
5. GA 35-312
6. GA 35A312
7. NACA65-412 a=0.5
8. GA 40-312
9. GA 40A312
10. GA 37A312
11. NACA65-412 a=0.6
12. NACA64-512 a=0.0
13. NACA64-412 a=0.8
14. MH 18 11.16%
15. NACA64-413 a=0.5
16. NACA64-411 a=0.5
17. NACA63-512 a=0.0
18. GA 35A311
19. EPPLER 207
20. NACA64-412 a=0.2
21. NACA63-412 a=0.8