Similarly shaped airfoils to GA 35A210
New! Bulk download of polars in Excel format: GA%2035A210.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. GA 40A210
3. GA 40-210
4. GA 37-210
5. RAF 28
6. NACA64-310 a=0.2
7. GA 30-210
8. GA 35-210
9. NACA64-310 a=0.5
10. RG 14 9.5%
11. GA 30A210
12. NACA63A310
13. HQ 1.5/10
14. NACA65-310 a=0.2
15. EM CY 1016 1510
16. NACA63-310 a=0.2
17. NACA64-310 a=0.0
18. NACA64-310 a=0.6
19. NACA63-310 a=0.5
20. TP210-10%
21. RG 14 10%