Similarly shaped airfoils to GA 40-217
New! Bulk download of polars in Excel format: GA%2040-217.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. NACA65-317 a=0.5
3. NACA65-317 a=0.6
4. GA 37A217
5. NACA65-317 a=0.8
6. NACA65-417
7. NACA65-317 a=0.2
8. NACA65-417 a=0.0
9. NACA65-317
10. GA 35A217
11. NACA64A317
12. GA 37-217
13. GA 40A216
14. GA 40-218
15. GA 40-216
16. GA 40A218
17. NACA65-318 a=0.5
18. NACA65-417 a=0.2
19. NACA65-318 a=0.6
20. GA 37A216
21. NACA65-317 a=0.0