Similarly shaped airfoils to GA 35-418
New! Bulk download of polars in Excel format: GA%2035-418.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. NACA63-518 a=0.6
3. NACA63-518 a=0.5
4. NACA64-518 a=0.6
5. NACA64-518 a=0.5
6. GA 35-419
7. GA 35-417
8. GA 37-417
9. NACA63-518 a=0.8
10. GA 37-419
11. NACA63-519 a=0.6
12. NACA63-517 a=0.6
13. NACA63-618
14. NACA63-618 a=0.5
15. NACA63-517 a=0.5
16. NACA63-718
17. NACA63-519 a=0.5
18. NACA64-618 a=0.5
19. NACA64-518 a=0.8
20. NACA64-718
21. FX 66-17AII-182