Similarly shaped airfoils to GA 35-213
New! Bulk download of polars in Excel format: GA%2035-213.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. NACA63-313 a=0.5
3. NACA63-313 a=0.6
4. NACA64-313 a=0.5
5. NACA63-313 a=0.2
6. NACA64-313 a=0.6
7. NACA63-313 a=0.8
8. NACA64-313 a=0.2
9. NACA63-313
10. NACA64-313 a=0.8
11. S8052 (11.88%)
12. NACA63-313 a=0.0
13. NACA64-313
14. GA 35A213
15. NACA63-413 a=0.0
16. NACA63-413
17. NACA64-313 a=0.0
18. HQ 1.5/12
19. GA 35-214
20. GA 35-212
21. NACA64-413 a=0.0