Similarly shaped airfoils to NACA64A212
New! Bulk download of polars in Excel format: NACA64A212.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (69) | 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. NACA65-212 a=0.8
3. NACA65(1)-212
4. NACA65-212 a=0.6
5. NACA65-212
6. NACA65A212
7. NACA65-212 a=0.5
8. NACA64-212 a=0.8
9. NACA65(1)-212 a=0.6
10. NACA64(1)-212
11. NACA64-212 a=0.6
12. NACA64-212
13. NACA65-312
14. NACA64-212 a=0.5
15. NACA65-212 a=0.2
16. HQ 1.0/12
17. AMSOIL2 RUTAN WING
18. NACA63-212 a=0.8
19. NACA65-212 a=0.0
20. NACA64A213
21. NACA64A211