Similarly shaped airfoils to NACA67A713
New! Bulk download of polars in Excel format: NACA67A713.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. NACA67A714
3. NACA67A712
4. NACA67-714 a=0.8
5. NACA66A713
6. NACA67-712 a=0.8
7. NACA66-713 a=0.8
8. NACA67-613 a=0.8
9. NACA66A714
10. NACA66-714 a=0.8
11. NACA67-713 a=0.6
12. NACA67A613
13. NACA67-613 a=0.6
14. NACA65A714
15. NACA67-612 a=0.8
16. NACA66-613 a=0.8
17. NACA65A713
18. NACA67-713
19. NACA67-714 a=0.6
20. NACA67A612
21. NACA67-614 a=0.8