Similarly shaped airfoils to GA 37-612
New! Bulk download of polars in Excel format: GA%2037-612.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 35A612
3. GA 40-612
4. GA 40A612
5. GA 37A612
6. NACA64-712 a=0.5
7. NACA63-712 a=0.5
8. NACA64-612 a=0.5
9. NACA64-612 a=0.6
10. GA 35A611
11. NACA63-612 a=0.5
12. NACA63-612 a=0.6
13. NACA64-712 a=0.6
14. NACA63-712 a=0.6
15. GA 37-613
16. GA 37-611
17. GA 37A611
18. GA 35-613
19. GA 40-611
20. GA 30-611
21. GA 40A611