Similarly shaped airfoils to GA 37-314
New! Bulk download of polars in Excel format: GA%2037-314.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. NACA64-414 a=0.5
3. NACA64-414 a=0.6
4. NACA63-414 a=0.5
5. NACA63-414 a=0.6
6. GA 35A314
7. GA 40-314
8. NACA64-414 a=0.8
9. GA 40A314
10. GA 37A314
11. NACA64-514
12. EPPLER 197
13. NACA63-414 a=0.8
14. GA 35A313
15. NACA63-514
16. NACA65-414 a=0.5
17. GA 37-313
18. GA 37-315
19. NACA65-414 a=0.6
20. NACA64-514 a=0.0
21. NACA64-413 a=0.5