Similarly shaped airfoils to NACA67A413
New! Bulk download of polars in Excel format: NACA67A413.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. NACA67-413 a=0.6
3. NACA67-413 a=0.5
4. NACA67-414 a=0.8
5. NACA67A414
6. NACA66A413
7. NACA67A412
8. NACA66-413 a=0.8
9. NACA67-412 a=0.8
10. NACA66-513
11. NACA66A414
12. NACA66-414 a=0.8
13. NACA67-313 a=0.8
14. NACA66-514
15. NACA67-313 a=0.6
16. NACA67-414 a=0.6
17. NACA67A313
18. NACA67-412 a=0.6
19. NACA66-413 a=0.6
20. NACA67A513
21. NACA66-413