Similarly shaped airfoils to GA 35-216
New! Bulk download of polars in Excel format: GA%2035-216.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. GA 37-216
3. NACA63-316 a=0.6
4. NACA64-316 a=0.5
5. NACA64-316 a=0.6
6. NACA63-316 a=0.8
7. NACA63-416
8. NACA64-316 a=0.8
9. NACA63-316 a=0.2
10. NACA63-416 a=0.0
11. NACA64-416
12. NACA63-316
13. NACA64-316 a=0.2
14. GA 35-215
15. GA 35-217
16. NACA64-416 a=0.0
17. NACA64-316
18. NACA63-317 a=0.5
19. NACA63-416 a=0.2
20. GA 37-215
21. NACA63-317 a=0.6