Similarly shaped airfoils to NACA66A716
New! Bulk download of polars in Excel format: NACA66A716.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. NACA65A716
3. NACA66A717
4. NACA66-717 a=0.8
5. NACA66A715
6. NACA66-715 a=0.8
7. NACA66-616 a=0.8
8. NACA65A717
9. NACA66-716 a=0.6
10. NACA67A715
11. NACA66A616
12. NACA67-715 a=0.8
13. EPPLER 662
14. NACA67A716
15. NACA67-716 a=0.8
16. NACA66-616 a=0.6
17. HQ-17
18. NACA66-615 a=0.8
19. NACA65A715
20. NACA65-717 a=0.8
21. NACA65-716 a=0.8