Similarly shaped airfoils to NACA66-212 a=0.2
New! Bulk download of polars in Excel format: NACA66-212%20a%3D0.2.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. NACA66-212 a=0.5
3. NACA66-212 a=0.6
4. NACA 66,2-(1.8)12 A=.6 P-51 TIP
5. MH 17
6. NACA66-212
7. NACA66(1)-212
8. NACA66A212
9. NACA66-212 a=0.8
10. NACA66-312 a=0.0
11. NACA67-212 a=0.2
12. NACA67-212 a=0.0
13. NACA66-213 a=0.2
14. NACA65A212
15. NACA66-211 a=0.2
16. NACA66-211 a=0.0
17. NACA66-213 a=0.0
18. NACA66-112 a=0.5
19. NACA67-211 a=0.2
20. NACA66-112 a=0.6
21. NACA67-212 a=0.5