Similarly shaped airfoils to GA 35-214
New! Bulk download of polars in Excel format: GA%2035-214.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. NACA63-314 a=0.5
3. NACA63-314 a=0.6
4. NACA64-314 a=0.5
5. NACA64-314 a=0.6
6. NACA63-314 a=0.8
7. NACA63-314 a=0.2
8. NACA64-314 a=0.8
9. NACA63-314
10. NACA64-314 a=0.2
11. NACA63-414
12. NACA63-414 a=0.0
13. NACA64-314
14. NACA63-314 a=0.0
15. NACA64-414
16. GA 35A214
17. GA 35-213
18. GA 35-215
19. NACA64-414 a=0.0
20. GA 37-213
21. NACA63-313 a=0.5