Similarly shaped airfoils to NACA67A415
New! Bulk download of polars in Excel format: NACA67A415.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. NACA67-415 a=0.6
3. NACA67-415 a=0.5
4. NACA67-416 a=0.8
5. NACA67A416
6. NACA67A414
7. NACA67-414 a=0.8
8. NACA67-315 a=0.8
9. NACA67-315 a=0.6
10. NACA66A415
11. NACA67A315
12. NACA66-415 a=0.8
13. NACA67-416 a=0.6
14. NACA67A515
15. NACA67-414 a=0.6
16. NACA66A416
17. NACA66-416 a=0.8
18. NACA66-515
19. NACA66-516
20. NACA66(215)-416
21. NACA67-615