Similarly shaped airfoils to GA 35-416
New! Bulk download of polars in Excel format: GA%2035-416.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. NACA63-516 a=0.5
3. NACA63-516 a=0.6
4. NACA64-516 a=0.6
5. NACA64-516 a=0.5
6. GA 35-415
7. GA 35-417
8. GA 37-415
9. NACA63-516 a=0.8
10. NACA63-515 a=0.5
11. MS3/15GPV
12. NACA63-515 a=0.6
13. NACA63-616
14. GA 37-417
15. GA 35A416
16. NACA63-517 a=0.6
17. NACA63-517 a=0.5
18. NACA64-515 a=0.5
19. NACA64-516 a=0.8
20. GA 35A415
21. NACA64-515 a=0.6