Similarly shaped airfoils to GA 35-220
New! Bulk download of polars in Excel format: GA%2035-220.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. NACA63-320 a=0.6
3. NACA63-320 a=0.5
4. NACA63-420
5. NACA64-320 a=0.6
6. NACA63-320 a=0.8
7. NACA64-320 a=0.5
8. NACA64-420
9. NACA64-320 a=0.8
10. GA 35-219
11. NACA63-420 a=0.2
12. NACA63-420 a=0.0
13. NACA63-320
14. NACA63-421
15. GA 37-219
16. NACA64-420 a=0.2
17. NACA63-320 a=0.2
18. NACA64-421
19. NACA64-420 a=0.0
20. NACA63-319 a=0.6
21. NACA63-319 a=0.5