Similarly shaped airfoils to NACA67A515
New! Bulk download of polars in Excel format: NACA67A515.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. NACA67-615
3. NACA67-515 a=0.6
4. NACA67-516 a=0.8
5. NACA67A516
6. NACA67A514
7. NACA67-514 a=0.8
8. NACA67-616
9. NACA67-614
10. NACA67-715
11. NACA67-415 a=0.8
12. NACA67-515 a=0.5
13. NACA66A515
14. NACA67-415 a=0.6
15. NACA66-515 a=0.8
16. NACA67A415
17. NACA66A516
18. NACA66-516 a=0.8
19. NACA66-615
20. NACA67A615
21. NACA66-616