Similarly shaped airfoils to NACA65-211
New! Bulk download of polars in Excel format: NACA65-211.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. NACA64A211
3. NACA64-211
4. NACA65-211 a=0.6
5. NACA63A211
6. NACA65-211 a=0.5
7. NACA65-211 a=0.0
8. NACA65-211 a=0.2
9. NACA65A211
10. NACA64-211 a=0.8
11. NACA65-111 a=0.6
12. NACA65-111 a=0.8
13. P-51D TIP (BL215)
14. NACA65-111 a=0.5
15. NACA64-211 a=0.6
16. NACA63-211
17. NACA64-211 a=0.5
18. NACA64-211 a=0.0
19. NACA64-211 a=0.2
20. NACA65-212
21. NACA65-210