Similarly shaped airfoils to GA 35-311
New! Bulk download of polars in Excel format: GA%2035-311.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. NACA63-411 a=0.5
3. NACA63-411 a=0.6
4. NACA64-411 a=0.5
5. MS2.5/11GPV
6. NACA64-411 a=0.6
7. GA 35A311
8. HN-203
9. NACA63-411 a=0.2
10. NACA63-411 a=0.8
11. NACA64-411 a=0.2
12. GA 37A311
13. GA 40-311
14. GA 30-310
15. GA 40A311
16. HN-955GS
17. HQ 2.5/11
18. NACA64-411 a=0.8
19. GA 35-310
20. GA 35-312
21. GA 35A310