Similarly shaped airfoils to NACA64A210
New! Bulk download of polars in Excel format: NACA64A210.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (9) | 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. NACA65-210 a=0.8
3. NACA65A210
4. NACA65-210 a=0.6
5. NACA65-210
6. NACA64-210 a=0.8
7. NACA65-210 a=0.5
8. NACA64-210 a=0.6
9. NACA64-210
10. NACA64-210 a=0.5
11. SB96VS 9.75/1.25
12. NACA63-210 a=0.8
13. NACA65-310
14. NACA65-210 a=0.2
15. HQ 1.0/10
16. NACA63-210 a=0.6
17. GOE 599
18. NACA63-210
19. NACA64-310
20. NACA65-210 a=0.0
21. NACA63-210 a=0.5