Similarly shaped airfoils to GA 37-420
New! Bulk download of polars in Excel format: GA%2037-420.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA64-520 a=0.6
3. GA 37-419
4. NACA64-520 a=0.5
5. NACA64-620 a=0.5
6. GA 35A419
7. NACA63-520 a=0.6
8. GA 35A420
9. NACA64-720
10. NACA64-620 a=0.6
11. NACA63-520 a=0.5
12. GA 35-419
13. GA 40-420
14. GA 40A420
15. NACA65-520 a=0.6
16. GA 37A419
17. NACA64-620 a=0.8
18. GA 37A420
19. NACA65-520 a=0.5
20. NACA63-620 a=0.5
21. NACA64-520 a=0.8