Similarly shaped airfoils to YS-900
New! Bulk download of polars in Excel format: ys900.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. NACA67-109 a=0.0
3. NACA67-109
4. NACA0010-65
5. NACA67-109 a=0.2
6. NACA67A109
7. NACA67-109 a=0.8
8. NACA67-109 a=0.5
9. NACA66-009
10. NACA67-109 a=0.6
11. NACA0010-34
12. NACA67-110 a=0.0
13. NACA67-110
14. Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft
15. NACA67-110 a=0.2
16. NACA67A110
17. MH 53
18. NACA67-110 a=0.8
19. NACA67-110 a=0.5
20. NACA0010-66
21. NACA67-110 a=0.6