Similarly shaped airfoils to GA 37A612


New! Bulk download of polars in Excel format: GA%2037A612.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 35A612
2. GA 40A612
3. GA 40-612
4. GA 37-612
5. NACA65-612 a=0.5
6. NACA65-712 a=0.5
7. NACA65-612 a=0.6
8. NACA64-712 a=0.5
9. GA 40A613
10. GA 37A613
11. GA 37A611
12. GA 37-613
13. GA 35-612
14. GA 40-613
15. GA 35A611
16. GA 30-612
17. GA 30U-612
18. GA 35A613
19. GA 30A612
20. NACA64-612 a=0.5
21. NACA64-612 a=0.6