Similarly shaped airfoils to NACA64(1)-212 MOD B
New! Bulk download of polars in Excel format: n64212mb.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. HQ 1.5/12
3. HQ 1.0/12
4. NACA2212
5. S8038 (13%)
6. NACA24012
7. EPPLER 360
8. NACA63-313 a=0.0
9. GA 30-212
10. ONERA NACA CAMBRE
11. NACA63-213 a=0.6
12. NACA63-213 a=0.5
13. NACA63-312 a=0.0
14. EPPLER 361
15. NACA63-213 a=0.8
16. NACA63-313
17. NACA63-212 a=0.5
18. NACA63-212 a=0.6
19. NACA63-212 a=0.8
20. NACA2312
21. NACA63-212 a=0.2