Similarly shaped airfoils to GA 35-414
New! Bulk download of polars in Excel format: GA%2035-414.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. NACA63-514 a=0.5
3. NACA63-514 a=0.6
4. S4233-136-84
5. NACA64-514 a=0.5
6. NACA64-514 a=0.6
7. GA 35A414
8. GA 35-413
9. GA 35-415
10. NACA63-513 a=0.5
11. NACA63-514 a=0.8
12. GA 37-413
13. MS3/13GPV
14. NACA63-513 a=0.6
15. NACA63-614
16. GA 35A413
17. GA 37-415
18. NACA64-513 a=0.5
19. GA 30-413.5
20. HQ 3.0/14
21. GA 30-413