Similarly shaped airfoils to GA 37-212
New! Bulk download of polars in Excel format: GA%2037-212.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. NACA64-312 a=0.5
3. NACA63-312 a=0.5
4. NACA64-312 a=0.6
5. NACA64-312 a=0.2
6. NACA63-312 a=0.6
7. GA 35A212
8. NACA63-312 a=0.2
9. GA 40-212
10. NACA64-312 a=0.8
11. GA 40A212
12. S8052 (11.88%)
13. GA 37A212
14. NACA63-312 a=0.8
15. NACA64-312
16. NACA64-312 a=0.0
17. HQ 1.5/12
18. NACA63-312
19. NACA63-312 a=0.0
20. GA 35A211
21. NACA65-312 a=0.5