Similarly shaped airfoils to GA 35-210
New! Bulk download of polars in Excel format: GA%2035-210.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. NACA63-310 a=0.2
3. NACA63-310 a=0.5
4. NACA63-310 a=0.6
5. NACA64-310 a=0.2
6. NACA63-310 a=0.0
7. NACA64-310 a=0.5
8. GA 35A210
9. HQ 1.5/10
10. NACA63-310
11. NACA64-310 a=0.6
12. NACA64-310 a=0.0
13. TP-CIEL-S
14. TP210-10%
15. NACA63-310 a=0.8
16. SB95 9.5/2
17. NACA64-310
18. MS2-9,5
19. GA 37A210
20. GA 40-210
21. RAF 28