Similarly shaped airfoils to NACA66A212
New! Bulk download of polars in Excel format: NACA66A212.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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. NACA66(1)-212
3. NACA 66,2-(1.8)12 A=.6 P-51 TIP
4. NACA66-212 a=0.6
5. NACA66-212
6. NACA66-212 a=0.5
7. NACA65A212
8. NACA66-312
9. NACA66-212 a=0.2
10. NACA66-212 a=0.0
11. NACA67A212
12. NACA67-212 a=0.8
13. NACA66-213 a=0.8
14. NACA66A213
15. NACA66A211
16. NACA66-211 a=0.8
17. NACA67-212 a=0.6
18. NACA65A213
19. NACA67A211
20. NACA67-211 a=0.8
21. NACA67-212