Similarly shaped airfoils to NACA65A211
New! Bulk download of polars in Excel format: NACA65A211.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. NACA66A211
3. NACA66-211 a=0.8
4. NACA65-211 a=0.8
5. NACA66-211 a=0.6
6. NACA65-211 a=0.6
7. NACA66-211
8. NACA65-211
9. NACA66-211 a=0.5
10. NACA63A211
11. NACA65-211 a=0.5
12. P-51D TIP (BL215)
13. NACA66-311
14. LOCKHEED C-141 BL426.57
15. NACA65-311
16. NACA0010-34 a=0.8 c(li)=0.2
17. NACA65-212 a=0.8
18. NACA66-211 a=0.2
19. NACA65(1)-212
20. NACA64A212
21. NACA65-211 a=0.2