Similarly shaped airfoils to NACA64-210
New! Bulk download of polars in Excel format: NACA64-210.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (16) | 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. NACA64-210 a=0.8
3. HQ 1.0/10
4. NACA63-210 a=0.8
5. NACA65-210
6. NACA63A210
7. NACA64-210 a=0.6
8. NACA64-210 a=0.5
9. NACA63-210 a=0.6
10. NACA64-210 a=0.0
11. NACA64A210
12. NACA64-210 a=0.2
13. NACA63-210 a=0.5
14. NACA65-210 a=0.8
15. NACA63-210 a=0.0
16. NACA63-210 a=0.2
17. NACA64-110 a=0.6
18. NACA64-110 a=0.8
19. NACA64-110 a=0.5
20. NACA63-110 a=0.6
21. NACA65-210 a=0.6