Similarly shaped airfoils to NACA66A713


New! Bulk download of polars in Excel format: NACA66A713.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
Dynamic plotter New!
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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1. NACA66-713 a=0.8
2. NACA65A713
3. NACA66A714
4. NACA66A712
5. NACA66-714 a=0.8
6. NACA66-712 a=0.8
7. NACA67A713
8. NACA67-713 a=0.8
9. NACA65A714
10. AH 88-K-130/20
11. NACA67A712
12. NACA67-712 a=0.8
13. NACA66-613 a=0.8
14. NACA65-713 a=0.8
15. NACA66-713 a=0.6
16. NACA65-714 a=0.8
17. FX 74-130 WP1
18. NACA64A713
19. NACA66A613
20. NACA65A712
21. NACA66-613 a=0.6