Similarly shaped airfoils to GA 35A212
New! Bulk download of polars in Excel format: GA%2035A212.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. GA 40A212
3. GA 40-212
4. GA 37-212
5. S8052 (11.88%)
6. NACA63A312
7. NACA64-312 a=0.5
8. NACA64A312
9. NACA64-312 a=0.6
10. S8055 (12%)
11. GA 30-212
12. NACA64-312 a=0.2
13. HQ 1.5/12
14. NACA65-312 a=0.5
15. GA 35-212
16. Ritz 2-30-12
17. NACA65-312 a=0.2
18. NACA63-312 a=0.5
19. GA 30A212
20. NACA65-312 a=0.6
21. GA 37-213