Similarly shaped airfoils to GA 40-210
New! Bulk download of polars in Excel format: GA%2040-210.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. GA 37A210
3. NACA65-310 a=0.2
4. GA 35A210
5. GA 37-210
6. NACA65-310 a=0.5
7. NACA65-310 a=0.0
8. NACA65-310 a=0.6
9. NACA64-310 a=0.2
10. NACA64-310 a=0.5
11. NACA65-310
12. NACA64-310 a=0.0
13. NACA64-310 a=0.6
14. NACA65-310 a=0.8
15. DP1.87/9.07_DS
16. NACA64A310
17. GA 35-210
18. NACA64-310
19. NACA63-310 a=0.2
20. NACA63A310
21. NACA64-310 a=0.8