Similarly shaped airfoils to GA 35-616
New! Bulk download of polars in Excel format: GA%2035-616.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. NACA63-716 a=0.5
3. NACA63-716 a=0.6
4. NACA64-716 a=0.5
5. NACA64-716 a=0.6
6. GOE 425
7. GA 35-615
8. GA 35-617
9. GA 37-615
10. FX 84-W-150
11. GA 37-617
12. GA 35A616
13. NACA63-715 a=0.5
14. GA 35A615
15. NACA64-715 a=0.5
16. NACA63-717 a=0.5
17. NACA63-715 a=0.6
18. GA 30-615
19. GA 30U-615
20. NACA63-717 a=0.6
21. NACA63-616 a=0.6