Similarly shaped airfoils to NACA65(1)-212
New! Bulk download of polars in Excel format: NACA65%281%29-212.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. NACA65-212
3. NACA64A212
4. NACA65-212 a=0.6
5. NACA65-212 a=0.5
6. NACA63A212
7. NACA64(1)-212
8. NACA65A212
9. NACA65(1)-212 a=0.6
10. NACA64-212 a=0.8
11. NACA64-212
12. NACA65-212 a=0.2
13. NACA65-312
14. NACA65-212 a=0.0
15. NACA64-212 a=0.6
16. NACA64-212 a=0.5
17. P-51D TIP (BL215)
18. NACA65A211
19. NACA65-211
20. NACA65-213 a=0.8
21. NACA65-211 a=0.8