Similarly shaped airfoils to GA 37A610
New! Bulk download of polars in Excel format: GA%2037A610.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 40A610
3. GA 40-610
4. GA 37-610
5. NACA65-610 a=0.5
6. NACA65-610 a=0.6
7. NACA64-610 a=0.5
8. GA 35-610
9. GA 30-610
10. NACA64-610 a=0.6
11. GA 30A610
12. GA 37-611
13. NACA63-610 a=0.5
14. GA 40A611
15. GA 40-611
16. GA 37A611
17. NACA63-610 a=0.6
18. NACA65-710 a=0.5
19. NACA64-710 a=0.5
20. GA 35A611
21. PSU 94-097 (AIAA 2001-2478)