Similarly shaped airfoils to NACA63A210
New! Bulk download of polars in Excel format: NACA63A210.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. NACA64-210 a=0.8
3. NACA65-210 a=0.8
4. NACA64-210 a=0.6
5. NACA65-210 a=0.6
6. NACA63-210 a=0.8
7. NACA64-210
8. NACA65-210
9. HQ 1.0/10
10. NACA64-210 a=0.5
11. NACA65-210 a=0.5
12. NACA65A210
13. SB96VS 9.75/1.25
14. NACA63-210 a=0.6
15. NACA63-210
16. NACA63-210 a=0.5
17. AIR 100-2 Acro MM 576 1999
18. GOE 599
19. NACA64-310
20. NACA64-211 a=0.8
21. RG-12