Similarly shaped airfoils to NACA64-317 a=0.6
New! Bulk download of polars in Excel format: NACA64-317%20a%3D0.6.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. NACA63-317 a=0.6
3. GA 37-217
4. NACA64-317 a=0.8
5. NACA63-317 a=0.5
6. GA 35-217
7. NACA64-417
8. NACA63-317 a=0.8
9. NACA63-417
10. NACA64-318 a=0.6
11. NACA64-317
12. NACA64-316 a=0.6
13. NACA64-316 a=0.5
14. NACA64-417 a=0.0
15. NACA64-318 a=0.5
16. NACA65-317 a=0.6
17. NACA64-317 a=0.2
18. NACA65-317 a=0.5
19. GA 37-216
20. NACA63-317
21. NACA63-316 a=0.6