Similarly shaped airfoils to NACA64-411 a=0.5
New! Bulk download of polars in Excel format: NACA64-411%20a%3D0.5.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. NACA64-411 a=0.6
3. NACA63-411 a=0.6
4. GA 37-311
5. GA 35-311
6. NACA65-411 a=0.5
7. GA 35A311
8. GA 40-311
9. GA 40A311
10. GA 37A311
11. NACA65-411 a=0.6
12. NACA64-511 a=0.0
13. NACA64-411 a=0.8
14. MS2.5/11GPV
15. NACA64-412 a=0.5
16. NACA64-410 a=0.5
17. NACA63-511 a=0.0
18. NACA63-411 a=0.8
19. GA 35A310
20. NACA64-411 a=0.2
21. NACA65-410 a=0.5