Similarly shaped airfoils to GA 37A210
New! Bulk download of polars in Excel format: GA%2037A210.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 40A210
3. GA 40-210
4. GA 37-210
5. NACA65-310 a=0.2
6. NACA65-310 a=0.5
7. RAF 28
8. NACA65-310 a=0.0
9. NACA64-310 a=0.2
10. NACA64A310
11. NACA64-310 a=0.5
12. NACA63A310
13. NACA65-310 a=0.6
14. NACA65-310
15. NACA64-310 a=0.0
16. NACA64-310 a=0.6
17. DP1.87/9.07_DS
18. SG6041
19. GA 35-210
20. RG 14 9.5%
21. GA 30-210