Similarly shaped airfoils to NACA64-415 a=0.6
New! Bulk download of polars in Excel format: NACA64-415%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. NACA63-415 a=0.6
3. GA 37-315
4. NACA63-415 a=0.5
5. GA 35-315
6. NACA64-415 a=0.8
7. NACA63-415 a=0.8
8. NACA64-515
9. NACA65-415 a=0.6
10. NACA63-515
11. GA 35A315
12. NACA65-415 a=0.5
13. NACA64-416 a=0.6
14. NACA64-414 a=0.6
15. GA 40-315
16. NACA64-414 a=0.5
17. NACA64(2)-415
18. GA 40A315
19. NACA64-416 a=0.5
20. NACA63-414 a=0.6
21. GA 35A314