Similarly shaped airfoils to NACA63-412 a=0.5
New! Bulk download of polars in Excel format: NACA63-412%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. NACA63-412 a=0.6
3. GA 35-312
4. GA 37-312
5. NACA64-412 a=0.6
6. GA 35A312
7. EPPLER 207
8. NM32 root
9. EPPLER 195
10. NACA63-512 a=0.0
11. NACA63-412 a=0.8
12. NACA63-413 a=0.5
13. NACA63-411 a=0.5
14. EPPLER 201
15. NACA64-512 a=0.0
16. GA 37A312
17. GA 35-313
18. GA 40-312
19. NACA65-412 a=0.5
20. NACA63-412 a=0.2
21. NACA64-412 a=0.8