Similarly shaped airfoils to GA 35-212
New! Bulk download of polars in Excel format: GA%2035-212.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. NACA63-312 a=0.5
3. NACA63-312 a=0.6
4. NACA63-312 a=0.2
5. NACA64-312 a=0.5
6. NACA64-312 a=0.6
7. S8052 (11.88%)
8. NACA64-312 a=0.2
9. NACA63-312 a=0.8
10. HQ 1.5/12
11. NACA63-312
12. NACA63-312 a=0.0
13. GA 35A212
14. NACA64-312 a=0.8
15. HN-980
16. SB95 11.5/2
17. NACA64-312
18. NACA64-312 a=0.0
19. NACA63-412 a=0.0
20. HQ 1.5/11
21. NACA63-412