Similarly shaped airfoils to NACA66A715
New! Bulk download of polars in Excel format: NACA66A715.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. NACA65A715
3. NACA66A716
4. NACA66A714
5. NACA66-716 a=0.8
6. NACA66-714 a=0.8
7. EPPLER 662
8. HQ-17
9. NACA65A716
10. NACA66-615 a=0.8
11. NACA67A714
12. NACA67-714 a=0.8
13. NACA66-715 a=0.6
14. NACA67A715
15. NACA67-715 a=0.8
16. NACA66A615
17. NACA66-615 a=0.6
18. NACA65-715 a=0.8
19. NACA65-716 a=0.8
20. NACA65A714
21. NACA66-614 a=0.8