Similarly shaped airfoils to NACA66-616 a=0.5
New! Bulk download of polars in Excel format: NACA66-616%20a%3D0.5.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. NACA66-617 a=0.5
3. NACA66-615 a=0.5
4. AH 93-156
5. NACA66-617 a=0.6
6. NACA66-615 a=0.6
7. NACA66-716 a=0.2
8. AH 94-156
9. AH 82-150 F
10. AH 83-159
11. NACA67-615 a=0.5
12. NACA66-516 a=0.6
13. NACA66-516 a=0.5
14. NACA67-616 a=0.5
15. NACA66-716 a=0.5
16. NACA67-615 a=0.6
17. NACA66-616 a=0.8
18. NACA67-616 a=0.6
19. NACA66A616
20. NACA66-716 a=0.0
21. NACA65-617 a=0.5