Similarly shaped airfoils to GA 40-311
New! Bulk download of polars in Excel format: GA%2040-311.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 37A311
3. NACA65-411 a=0.5
4. GA 35A311
5. NACA65-411 a=0.6
6. GA 37-311
7. NACA64-411 a=0.5
8. NACA64-411 a=0.6
9. NACA65-411 a=0.2
10. EPPLER 374
11. NACA65-411 a=0.8
12. NACA63-411 a=0.5
13. GA 35-311
14. NACA64A411
15. NACA64-411 a=0.2
16. GA 40A310
17. GA 40-310
18. GA 40-312
19. NACA63-411 a=0.6
20. GA 37A310
21. NACA65-311 a=0.6