Similarly shaped airfoils to NACA64-311
New! Bulk download of polars in Excel format: NACA64-311.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
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2. HQ 1.5/11
3. NACA65-311
4. NACA64-211 a=0.8
5. NACA64-211 a=0.6
6. NACA63-211 a=0.8
7. NACA64-311 a=0.8
8. GA 37-211
9. NACA63-211 a=0.6
10. NACA63-311 a=0.8
11. NACA64-211 a=0.5
12. GA 35-211
13. NACA63A311
14. NACA63-211 a=0.5
15. NACA65-211 a=0.8
16. EM CY 1016 1510
17. GA 35A211
18. NACA63A211
19. GA 40-211
20. NACA65-211 a=0.6
21. NACA64A311