Similarly shaped airfoils to GA 37A620


New! Bulk download of polars in Excel format: GA%2037A620.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

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1. GA 35A620
2. GA 40A620
3. GA 40-620
4. GA 37A619
5. GA 35A619
6. NACA65-720 a=0.5
7. NACA65-720 a=0.6
8. GA 37-620
9. GA 40A619
10. GA 40-619
11. NACA64A720
12. NACA65-719 a=0.5
13. NACA63A720
14. NACA65-719 a=0.6
15. GOE 424
16. NACA65-720 a=0.8
17. NACA64-720 a=0.6
18. GA 30-619
19. NACA64-720 a=0.5
20. GA 35-620
21. NACA65-620 a=0.6