Similarly shaped airfoils to GA 37-219
New! Bulk download of polars in Excel format: GA%2037-219.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. NACA64-319 a=0.6
3. NACA64-319 a=0.5
4. NACA64-419
5. NACA64-319 a=0.8
6. NACA63-319 a=0.6
7. NACA63-319 a=0.5
8. NACA63-419
9. NACA63-319 a=0.8
10. GA 37-218
11. GA 37-220
12. NACA64-419 a=0.2
13. GA 35A219
14. NACA64-419 a=0.0
15. GA 35A218
16. NACA64-320 a=0.6
17. NACA64-320 a=0.5
18. NACA64-319
19. NACA64-420
20. NACA65-319 a=0.5
21. GA 35-220