Similarly shaped airfoils to GA 35-016
New! Bulk download of polars in Excel format: GA%2035-016.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. EPPLER 477
3. EPPLER 837 HYDROFOIL
4. NACA63-116 a=0.0
5. NACA63-116
6. NACA64-116 a=0.0
7. NACA63-116 a=0.2
8. NACA64-116
9. GA 35-015
10. GA 35-017
11. NACA63-015
12. NACA64-116 a=0.2
13. GA 37-015
14. FX 71-L-150/25
15. NACA64-015
16. NACA63A016
17. GA 37-017
18. GA 35A016
19. FX 71-L-150/30
20. NACA63-116 a=0.8
21. NACA63-116 a=0.5