Similarly shaped airfoils to GA 37A417


New! Bulk download of polars in Excel format: GA%2037A417.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
1. GA 35A417
2. GA 40A417
3. GA 40-417
4. NACA65-517 a=0.5
5. NACA65-517 a=0.6
6. GA 37A418
7. GA 37A416
8. GA 40A418
9. GA 35A416
10. GA 37-417
11. GA 40-418
12. GA 35A418
13. NACA64A517
14. GA 37-418
15. NACA63A517
16. NACA65-518 a=0.6
17. NACA65-518 a=0.5
18. GA 40A416
19. NACA65-517 a=0.8
20. NACA64-517 a=0.6
21. NACA65-617