Similarly shaped airfoils to GA 35-612
New! Bulk download of polars in Excel format: GA%2035-612.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. NACA63-712 a=0.5
3. GA 35A612
4. NACA64-712 a=0.5
5. NACA63-612 a=0.5
6. NACA63-612 a=0.6
7. NACA63-712 a=0.6
8. NACA64-612 a=0.5
9. GA 35-611
10. GA 35-613
11. NACA64-612 a=0.6
12. GA 30-611
13. GA 35A611
14. GA 37-611
15. GA 37A612
16. GA 40-612
17. NACA64-712 a=0.6
18. GA 37-613
19. GA 40A612
20. GA 30-612
21. GA 30U-612