Similarly shaped airfoils to GA 40-417
New! Bulk download of polars in Excel format: GA%2040-417.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. NACA65-517 a=0.5
3. NACA65-517 a=0.6
4. GA 37A417
5. GA 35A417
6. GA 37-417
7. GA 40A416
8. GA 40-418
9. GA 40-416
10. GA 40A418
11. NACA65-517 a=0.8
12. GA 37A416
13. NACA65-516 a=0.5
14. NACA65-617
15. NACA65-516 a=0.6
16. NACA65-518 a=0.6
17. NACA65-518 a=0.5
18. GA 37-418
19. NACA64-517 a=0.6
20. GA 35A416
21. NACA64-517 a=0.5