Similarly shaped airfoils to NACA63A212
New! Bulk download of polars in Excel format: NACA63A212.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (15) | 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. NACA64-212 a=0.8
3. NACA65-212 a=0.8
4. NACA65(1)-212
5. NACA64(1)-212
6. NACA64-212 a=0.6
7. NACA65-212 a=0.6
8. HQ 1.0/12
9. NACA65-212
10. NACA64-212
11. NACA64-212 a=0.5
12. NACA65-212 a=0.5
13. NACA63-212 a=0.8
14. NACA65(1)-212 a=0.6
15. NACA65A212
16. NACA63-212 a=0.6
17. NACA64-213 a=0.8
18. NACA63-212
19. NACA64-312
20. NACA63-212 a=0.5
21. NACA64-213 a=0.6