Similarly shaped airfoils to GA 40A410
New! Bulk download of polars in Excel format: GA%2040A410.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
Dynamic plotter New!
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 37A410
3. GA 35A410
4. NACA65-510 a=0.5
5. GA 37-410
6. NACA64-510 a=0.5
7. NACA65-510 a=0.6
8. NACA64-510 a=0.6
9. NACA63-510 a=0.5
10. GA 35-410
11. NACA63-510 a=0.6
12. NACA65-410 a=0.6
13. GA 40-411
14. GOE 595
15. GA 40A411
16. S3024 9.84%
17. NACA65-410 a=0.5
18. GA 37-411
19. NACA65-510 a=0.2
20. EPPLER 193
21. NACA65-509 a=0.5