Similarly shaped airfoils to GA 40-620
New! Bulk download of polars in Excel format: GA%2040-620.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. NACA65-720 a=0.5
3. GA 37A620
4. NACA65-720 a=0.6
5. GA 40-619
6. GA 40A619
7. GA 35A620
8. GA 37A619
9. GA 37-620
10. NACA65-719 a=0.5
11. NACA65-719 a=0.6
12. GA 35A619
13. NACA65-720 a=0.8
14. NACA65-620 a=0.6
15. NACA65-620 a=0.5
16. NACA64-720 a=0.6
17. NACA64-720 a=0.5
18. NACA64A720
19. GA 37-619
20. GA 35-620
21. NACA65-619 a=0.6