Similarly shaped airfoils to GA 35-614
New! Bulk download of polars in Excel format: GA%2035-614.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. NACA63-714 a=0.5
3. NACA64-714 a=0.5
4. NACA63-714 a=0.6
5. NACA64-714 a=0.6
6. GA 35A614
7. GA 35-613
8. GA 35-615
9. GOE 426
10. GA 37-613
11. NACA63-614 a=0.6
12. FX 84-W-140
13. GA 35A613
14. GA 37-615
15. GOE 758
16. GOE 549
17. GA 30-613
18. NACA63-614 a=0.5
19. NACA63-713 a=0.5
20. NACA64-614 a=0.6
21. GA 37A614